Airworthiness Directives; Textron Aviation Inc. Airplanes, 6114-6118 [2018-02551]

Download as PDF 6114 Federal Register / Vol. 83, No. 30 / Tuesday, February 13, 2018 / Rules and Regulations (d) Subject Air Transport Association of America (ATA) Code 28: Fuel. (e) Reason This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as nonconforming fuel tank caps. We are issuing this AD to detect and address nonconforming fuel tank caps, which could result in fuel loss and lead to fuel starvation and inflight engine shutdown. sradovich on DSK3GMQ082PROD with RULES (f) Actions and Compliance Unless already done, do the following actions. (1) Within 15 days after March 5, 2018 (the effective date of this AD), insert the CAA, Civil Aviation Authority of New Zealand, Supplement to AIR 2825 and AIR 3237, Section 2, Limitations, Revision 1, dated December 8, 2017, into the pilot’s operating handbook/airplane flight manual (POH/ AFM). (2) Within 45 days after March 5, 2018 (the effective date of this AD), inspect the fuel tank caps, part number (P/N) 457–1015–12, following the Accomplishment Instructions in Pacific Aerospace Mandatory Service Bulletin, PACSB/XL/089, Issue 01, dated December 8, 2017. (3) If a damaged or non-conforming fuel tank cap is found during the inspection required in paragraph (f)(2) of this AD, before further flight, replace any damaged or nonconforming fuel tank cap with a modified fuel tank cap, P/N 11–21087–1. (4) After replacement of damaged or nonconforming fuel tank caps with P/N 11– 21087–1, as required in paragraph (f)(3) of this AD, remove the CAA Supplement to AIR 2825 and AIR 3237, Section 2, Limitations, Revision 1, dated December 8, 2017, from the POH/AFM. (5) Replacement of damaged or nonconforming fuel tank caps with P/N 11– 21087–1, as required in paragraph (f)(3) of this AD, terminates the repetitive inspections required in the CAA Supplement to AIR 2825 and AIR 3237, Section 2, Limitations, Revision 1, dated December 8, 2017. (6) Long-range aircraft delivery ferry flights and oceanic flights are prohibited until the inspection required in paragraph (f)(2) of this AD and any necessary replacements required by paragraph (f)(3) of this AD have been completed. (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Small Airplane Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4144; fax: (816) 329–4090; email: mike.kiesov@faa.gov. Before using any VerDate Sep<11>2014 15:52 Feb 12, 2018 Jkt 244001 approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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, Small Airplane Standards Branch, FAA; or the CAA, which is the aviation authority for New Zealand. (h) Related Information Refer to MCAI from the CAA, AD DCA/ 750XL/20, dated December 8, 2017; Pacific Aerospace Mandatory Service Bulletin PACSB/XL/089, Issue 01, dated December 8, 2017; and CAA Supplement to AIR 2825 and AIR 3237 (POH/AFM), Section 2, Limitations, Revision 1, dated December 8, 2017, for related information. You may examine the MCAI on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018–0066. (i) 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 the AD specifies otherwise. (i) Pacific Aerospace Mandatory Service Bulletin PACSB/XL/089, Issue 01, dated December 8, 2017. (ii) CAA, Civil Aviation Authority of New Zealand, Supplement to AIR 2825 and AIR 3237, Section 2, Limitations, Revision 1, dated December 8, 2017. (3) For service information identified in this AD, contact Pacific Aerospace Limited, Airport Road, Hamilton, Private Bag 3027, Hamilton 3240, New Zealand; phone: +64 7843 6144; fax: +64 843 6134; email: pacific@ aerospace.co.nz; internet: www.aerospace.co.nz. (4) You may view this referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the internet at http://www.regulations.gov by searching for locating Docket No. FAA–2018– 0066. (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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Kansas City, Missouri, on January 25, 2018. Melvin J. Johnson, Deputy Director, Policy & Innovation Division, Aircraft Certification Service. [FR Doc. 2018–02611 Filed 2–12–18; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0068; Product Identifier 2017–CE–049–AD; Amendment 39–19176; AD 2018–03–03] RIN 2120–AA64 Airworthiness Directives; Textron Aviation Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A 421, 421A, 421B, 421C, and 425 airplanes. This AD requires repetitively inspecting the left and the right forward lower carry through spar cap for cracks and replacing the carry through spar if cracks are found. This AD was prompted by a report of a fully cracked lower forward carry through spar cap found on an affected airplane. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 28, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 28, 2018. We must receive comments on this AD by March 30, 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact Textron Aviation Inc., Textron Aviation Customer Service, One Cessna Blvd., Wichita, Kansas 67215; telephone: (316) 517– 5800; email: customercare@txtav.com; SUMMARY: E:\FR\FM\13FER1.SGM 13FER1 Federal Register / Vol. 83, No. 30 / Tuesday, February 13, 2018 / Rules and Regulations internet: www.txtav.com. You may view this service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329– 4148. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0068. 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– 0068; 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 street address for Docket Operations (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Bobbie Kroetch, Aerospace Engineer, Wichita ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4155; fax: (316) 946–4107; email: bobbie.kroetch@ faa.gov or Wichita-COS@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We received a report of a fully cracked lower forward carry through spar cap found on a Textron Aviation Inc. (type certificate previously held by Cessna Aircraft Company) Model 402C airplane. Investigation revealed that the crack is a result of metal fatigue. At this time, the cracking has only been found on the Model 402C airplanes. However, the carry through spar cap and surrounding structure on the other model airplanes included in this AD are similar and the loads on the other model airplanes are similar to (or higher than) the Model 402C airplanes. This condition, if not addressed, could cause failure of the carry through spar cap during flight and result in loss of control. We are issuing this AD to address the unsafe condition on these products. 6115 Related Service Information Under 1 CFR Part 51 approved, and available, we may consider additional rulemaking. We reviewed Textron Aviation Multiengine Mandatory Service Letter MEL– 57–01 and Textron Aviation Conquest Mandatory Service Letter CQL–57–01, both dated December 18, 2017. As applicable, these service letters describe procedures for repetitively inspecting the forward lower carry through spar cap for cracks. 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 Justification and Determination of the Effective Date Other Related Service Information We reviewed Textron Aviation Conquest Service Bulletin CQB–57–01, Textron Aviation Multi-engine Service Bulletin MEB–57–01, and Textron Multi-engine Service Bulletin MEB–57– 02, all dated December 20, 2017. As applicable, these service bulletins provide the manufacturer’s optional procedures for installing access panels for easier access to the forward lower carry through spars. This AD does not require installing the access panels. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires repetitively inspecting the left and the right forward lower carry through spar cap for cracks and replacing the carry through spar if cracks are found. This AD also requires sending the inspection results to the FAA. Interim Action We consider this AD interim action. Textron Aviation Inc. is evaluating the initial and repetitive inspection intervals, as well as designing a replacement lower carry through spar cap from an improved material. After the evaluations are complete and the design modification is developed, An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because cracks in the left and/or the right forward lower carry through spar cap could cause the carry through spar cap to fail during flight and result in loss of control. Therefore, we find good cause that notice and opportunity for prior public comment are impracticable. In addition, for the reason stated above, we find that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA–2018–0068 and Product Identifier 2017–CE–049–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this final rule. We will consider all comments received by the closing date and may amend this final rule because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this final rule. Costs of Compliance We estimate that this AD affects 2,147 airplanes of U.S. registry. We estimate the following costs to comply with this AD: sradovich on DSK3GMQ082PROD with RULES ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspect the left and the right forward lower carry through spar cap for cracks (without inspection access panels). 12 work-hours × $85 per hour = $1,020 per inspection cycle. Not applicable ....... $1,020 per inspection cycle. $2,189,940 per inspection cycle. VerDate Sep<11>2014 15:52 Feb 12, 2018 Jkt 244001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\13FER1.SGM 13FER1 6116 Federal Register / Vol. 83, No. 30 / Tuesday, February 13, 2018 / Rules and Regulations We estimate the following costs to do any necessary replacement that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need this replacements: ON-CONDITION COSTS Action Labor cost Replace carry through spar .......................................... 800 work-hours × $85 per hour = $68,000 .................. sradovich on DSK3GMQ082PROD with RULES Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW, Washington, DC 20591. ATTN: Information Collection Clearance Officer, AES–200. 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 VerDate Sep<11>2014 15:52 Feb 12, 2018 Jkt 244001 Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to small airplanes, gliders, balloons, airships, domestic business jet transport airplanes, and associated appliances to the Director of the Policy and Innovation 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 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 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): ■ 2018–03–03 Textron Aviation Inc.: Amendment 39–19176; Docket No. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Parts cost Cost per product $5,000 $73,000 FAA–2018–0068; Product Identifier 2017–CE–049–AD. (a) Effective Date This AD is effective February 28, 2018. (b) Affected ADs None. (c) Applicability This AD applies to the following Textron Aviation Inc. (type certificate previously held by Cessna Aircraft Company) model airplanes, that are certificated in any category: TABLE 1 TO PARAGRAPH (C) OF THIS AD—AFFECTED MODELS AND SERIAL NUMBERS Model Serial numbers 401 ..... 401A ... 401B ... 402 ..... 402A ... 402B ... 402C ... 411 ..... 411A ... 414 ..... 414A ... 421 ..... 421A ... 421B ... 421C ... 425 ..... 401–0001 through 401–0322 401A0001 through 401A0132 401B0001 through 401B0221 402–0001 through 402–0322 402A0001 through 402A0129 402B0001 through 402B1384 689, 402C0001 through 402C1020 411–0001 through 411–0250 411–0251 through 411–0300 414–0001 through 414–0965 414A0001 through 414A1212 421–0001 through 421–0200 421A0001 through 421A0158 421B0001 through 421B0970 421C0001 through 421C1807 425–0001 through 425–0236 (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report that a fully cracked lower forward carry through spar cap was found on a Textron Model 402C airplane. We are issuing this AD to prevent failure of the carry through spar cap during flight. The unsafe condition, if not addressed, could result in loss of control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Initial Inspection for All Affected Airplanes With 24,975 Hours Time-InService (TIS) or More on the Carry Through Spars Within the next 25 hours TIS after February 28, 2018 (the effective date of this E:\FR\FM\13FER1.SGM 13FER1 Federal Register / Vol. 83, No. 30 / Tuesday, February 13, 2018 / Rules and Regulations AD), do a detailed visual inspection of the left and right forward lower carry through spar cap for cracks. Using a 10X magnifier visually inspect the bottom surface of the carry through spar cap in the areas around the fasteners located just inboard of the lefthand and right-hand forward lower wing fittings. If a crack is not positively identified during the detailed visual inspection but is suspected or the area is questionable, before further flight, do a surface eddy current inspection of the suspected area. Do these inspections using the Accomplishment Instructions in Textron Aviation Multiengine Mandatory Service Letter MEL–57–01 and Textron Aviation Conquest Mandatory Service Letter CQL–57–01, both dated December 18, 2017, as applicable. sradovich on DSK3GMQ082PROD with RULES (h) Initial Inspection for All Affected Airplanes With Less Than 24,975 Hours TIS on the Carry Through Spars Using the compliance times listed in paragraphs (h)(1) through (3) of this AD, do a detailed visual inspection of the left and right forward lower carry through spar cap for cracks. Using a 10X magnifier visually inspect the bottom surface of the carry through spar cap in the areas around the fasteners located just inboard of the left-hand and right-hand forward lower wing fittings. If a crack is not positively identified during the detailed visual inspection but is suspected or the area is questionable, before further flight, do a surface eddy current inspection of the suspected area. Do these inspections using the Accomplishment Instructions in Textron Aviation Multiengine Mandatory Service Letter MEL–57–01 and Textron Aviation Conquest Mandatory Service Letter CQL–57–01, both dated December 18, 2017, as applicable. (1) For Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A, 421, and 421A airplanes: Before the accumulation of 15,000 TIS on the carry through spars or within the next 50 hours TIS after February 28, 2018 (the effective date of this AD), whichever occurs later. (2) For Models 421B and 421C airplanes: Before the accumulation of 12,000 hours TIS on the carry through spars or within the next 50 hours TIS after February 28, 2018 (the effective date of this AD), whichever occurs later. (3) For Model 425 airplanes: Before the accumulation of 11,000 TIS on the carry through spars or within the next 50 hours TIS after February 28, 2018 (the effective date of this AD), whichever occurs later. (i) Repetitive Inspections for All Affected Airplanes If no cracks are found during the detailed visual inspections or the surface eddy current inspections required in paragraphs (g) and (h) of this AD, repetitively thereafter inspect at intervals not to exceed 50 hours TIS. Inspect as specified in paragraphs (g) and (h) of this AD using the service information specified in each paragraph as applicable. (j) Replacement of Carry Through Spars for All Affected Airplanes If cracks are found during any inspection required in paragraphs (g) through (i) and VerDate Sep<11>2014 15:52 Feb 12, 2018 Jkt 244001 paragraph (k) of this AD, before further flight, replace the carry through spar. (k) Initial and Repetitive Inspections of Newly Replaced Carry Through Spars for All Affected Airplanes At the compliance times in paragraphs (k)(1) through (3) of this AD, do a detailed visual inspection of the left and right forward lower carry through spar cap for cracks. Using a 10X magnifier visually inspect the bottom surface of the carry through spar cap in the areas around the fasteners located just inboard of the left-hand and right-hand forward lower wing fittings. If a crack is not positively identified during the detailed visual inspection but is suspected or the area is questionable, before further flight, do a surface eddy current inspection of the suspected area. Do these inspections using the Accomplishment Instructions in Textron Aviation Multi-engine Mandatory Service Letter MEL–57–01 and Textron Aviation Conquest Mandatory Service Letter CQL–57– 01, both dated December 18, 2017, as applicable. (1) For Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A, 421, and 421A airplanes: Before the accumulation of 15,000 hours TIS on the newly installed carry through spar. If no cracks are found, repetitively thereafter inspect at intervals not to exceed 50 hours TIS. (2) For Models 421B and 421C airplanes: Before the accumulation of 12,000 hours TIS on the newly installed carry through spar. If no cracks are found, repetitively thereafter inspect at intervals not to exceed 50 hours TIS. (3) For Model 425 airplanes: Before the accumulation of 11,000 hours TIS on the newly installed carry through spar. If no cracks are found, repetitively thereafter inspect at intervals not to exceed 50 hours TIS. (l) Reporting Requirement for All Affected Airplanes Within 30 days after each inspection required by paragraphs (g) through (i) and paragraph (k) of this AD, report the results of the inspection to the FAA representative identified in paragraph (q) of this AD using the undated Attachment (titled Spar Cap Inspection Results Form and Spar Cap Inspection Results Form Continued) to Textron Aviation Multi-engine Mandatory Service Letter MEL–57–01 and Textron Aviation Conquest Mandatory Service Letter CQL–57–01, both dated December 18, 2017, as applicable. Please identify AD 2018–03–03 in the subject line if submitted through email. (m) Installation of Optional Access Panels All Affected Airplanes Textron Aviation Conquest Service Bulletin CQB–57–01, Textron Aviation Multi-engine Service Bulletin MEB–57–01, and Textron Multi-engine Service Bulletin MEB–57–02, all dated December 20, 2017, provide the manufacturer’s optional procedures for installing access panels for easier access to the forward carry through spars. This AD does not require installing the access panels, but does not restrict the owner/operator from doing so. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 6117 (n) Credit for Actions Done Following Previous Service Information for Affected Airplanes This AD allows credit for the initial inspection of the forward lower carry through spar cap required in paragraphs (g) and (h) of this AD if done before February 28, 2018 (the effective date of this AD) using the following documents: (1) Models 401, 401A, 401B, 402, 402A, 402B airplanes: Cessna Aircraft Company Model 401/402 Supplemental Inspection Document, Supplemental Inspection Number 57–10–10, dated June 3, 2002. (2) Model 402C airplanes: Cessna Aircraft Company Model 402C Maintenance Manual, Supplemental Inspection Number 57–10–14, dated June 3, 2002. (3) Models 411 and 411A airplanes: Cessna Aircraft Company Model 411, Supplemental Inspection Document, Supplemental Inspection Number 57–10–10, dated January 6, 2003. (4) Model 414 airplanes: Cessna Aircraft Company Model 414 Supplemental Inspection Document, Supplemental Inspection Number 57–10–10, dated August 1, 2002. (5) Model 414A airplanes: Cessna Aircraft Company Model 414A Supplemental Inspection Document, Supplemental Inspection Number 57–10–14, dated August 1, 2002. (6) Models 421, 421A, and 421B airplanes: Cessna Aircraft Company Model 421 Supplemental Inspection Document, Supplemental Inspection Number 57–10–10, dated March 3, 2003. (7) Model 421C airplanes: Cessna Aircraft Company Model 421C Supplemental Inspection Document, Supplemental Inspection Number 57–10–14, dated January 6, 2003. (o) Paperwork Reduction Act Burden Statement A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 15 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (p) Alternative Methods of Compliance (AMOCs) (1) The Manager, Wichita ACO 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 E:\FR\FM\13FER1.SGM 13FER1 6118 Federal Register / Vol. 83, No. 30 / Tuesday, February 13, 2018 / Rules and Regulations principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (q) of this AD. (2) 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. (q) Related Information For more information about this AD, contact Bobbie Kroetch, Aerospace Engineer, Wichita ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4155; fax: (316) 946–4107; email: bobbie.kroetch@faa.gov or Wichita-COS@ faa.gov. (r) Material Incorporated by Reference sradovich on DSK3GMQ082PROD with RULES (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) Textron Aviation Multi-engine Mandatory Service Letter MEL–57–01, dated December 18, 2017 (includes the undated Attachment titled Spar Cap Inspection Results Form and Spar Cap Inspection Results Form Continued). (ii) Textron Aviation Conquest Mandatory Service Letter CQL–57–01, dated December 18, 2017 (includes the undated Attachment titled Spar Cap Inspection Results Form and Spar Cap Inspection Results Form Continued). (3) For Textron Aviation service information identified in this AD, contact Textron Aviation Inc., Textron Aviation Customer Service, One Cessna Blvd., Wichita, Kansas 67215; telephone: (316) 517– 5800; email: customercare@txtav.com; internet: www.txtav.com. (4) You may view this service information at FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. (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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Kansas City, Missouri, on February 2, 2018. Melvin J. Johnson, Deputy Director, Policy & Innovation Division, Aircraft Certification Service. [FR Doc. 2018–02551 Filed 2–12–18; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 15:52 Feb 12, 2018 Jkt 244001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0952; Product Identifier 2017–CE–028–AD; Amendment 39–19189; AD 2018–03–16] RIN 2120–AA64 Airworthiness Directives; Stemme AG Gliders Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2017–10– 11 for Stemme AG Model Stemme S10– VT gliders (type certificate previously held by Stemme GmbH & Co. KG). This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as certain propeller front transmission gear wheels having insufficient material strength because of improper heat treatment during manufacturing. We are issuing this AD to require actions to address the unsafe condition on these products and to add Stemme AG Model Stemme S 12 gliders to the Applicability section. DATES: This AD is effective March 20, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 20, 2018. ADDRESSES: You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0952; or in person at Docket Operations, U.S. Department of Transportation, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. For service information identified in this AD, contact STEMME AG, Flugplatzstrasse F2, Nr. 6–7, D–15344 Strausberg, Germany; telephone: +49 (0) 3341 3612–0, fax: +49 (0) 3341 3612–30; internet: https://www.stemme.com. You may view this referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the internet at http:// www.regulations.gov by searching for Docket No. FAA–2017–0952. SUMMARY: PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4165; fax: (816) 329–4090; email: jim.rutherford@faa.gov. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Stemme AG Model Stemme S10–VT gliders (type certificate previously held by Stemme GmbH & Co. KG) and all Stemme AG Model Stemme S 12 gliders equipped with a certain front gearbox, part number 11AG. That NPRM was published in the Federal Register on October 10, 2017 (82 FR 46938), and proposed to supersede AD 2017–10–11, Amendment 39–18885 (82 FR 24239, May 26, 2017) (‘‘AD 2017– 10–11’’). Since we issued AD 2017–10–11, we have type certificated Stemme AG Model Stemme S 12 gliders in the United States and have determined those model gliders should also be included in the applicability of AD 2017–10–11. In addition, Stemme AG has issued new service information with procedures for addressing the unsafe condition. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the proposal and the FAA’s response to the comment. Request for Manufacturer To Be Responsible for All Associated Cost Taylor Ray stated that the manufacturer should be responsible for replacing the front gearbox on the affected gliders at no cost to the owners/ operators. We infer that the commenter is referring to the cost for both parts and labor. Taylor Ray stated that since the unsafe condition resulted from the manufacturing process, the manufacturer should be responsible for fixing the unsafe condition. We neither agree nor disagree since the FAA does not get involved in who pays for the cost of mitigating an unsafe condition. The primary concern the FAA has when issuing an AD is addressing unsafe conditions on various aircraft flying in the United States. While we provide information related to the estimated labor and parts cost associated with each AD, we do not control warranty coverage for owner/ operators of the affected aircraft nor can E:\FR\FM\13FER1.SGM 13FER1

Agencies

[Federal Register Volume 83, Number 30 (Tuesday, February 13, 2018)]
[Rules and Regulations]
[Pages 6114-6118]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-02551]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0068; Product Identifier 2017-CE-049-AD; Amendment 
39-19176; AD 2018-03-03]
RIN 2120-AA64


Airworthiness Directives; Textron Aviation Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Textron Aviation Inc. Models 401, 401A, 401B, 402, 402A, 402B, 402C, 
411, 411A, 414, 414A 421, 421A, 421B, 421C, and 425 airplanes. This AD 
requires repetitively inspecting the left and the right forward lower 
carry through spar cap for cracks and replacing the carry through spar 
if cracks are found. This AD was prompted by a report of a fully 
cracked lower forward carry through spar cap found on an affected 
airplane. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective February 28, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 28, 
2018.
    We must receive comments on this AD by March 30, 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this final rule, contact 
Textron Aviation Inc., Textron Aviation Customer Service, One Cessna 
Blvd., Wichita, Kansas 67215; telephone: (316) 517-5800; email: 
[email protected];

[[Page 6115]]

internet: www.txtav.com. You may view this service information at the 
FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the FAA, 
call (816) 329-4148. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0068.

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-
0068; 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 street address for Docket Operations (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Bobbie Kroetch, Aerospace Engineer, 
Wichita ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas 67209; 
telephone: (316) 946-4155; fax: (316) 946-4107; email: 
[email protected] or [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We received a report of a fully cracked lower forward carry through 
spar cap found on a Textron Aviation Inc. (type certificate previously 
held by Cessna Aircraft Company) Model 402C airplane. Investigation 
revealed that the crack is a result of metal fatigue. At this time, the 
cracking has only been found on the Model 402C airplanes. However, the 
carry through spar cap and surrounding structure on the other model 
airplanes included in this AD are similar and the loads on the other 
model airplanes are similar to (or higher than) the Model 402C 
airplanes.
    This condition, if not addressed, could cause failure of the carry 
through spar cap during flight and result in loss of control. We are 
issuing this AD to address the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    We reviewed Textron Aviation Multi-engine Mandatory Service Letter 
MEL-57-01 and Textron Aviation Conquest Mandatory Service Letter CQL-
57-01, both dated December 18, 2017. As applicable, these service 
letters describe procedures for repetitively inspecting the forward 
lower carry through spar cap for cracks. 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.

Other Related Service Information

    We reviewed Textron Aviation Conquest Service Bulletin CQB-57-01, 
Textron Aviation Multi-engine Service Bulletin MEB-57-01, and Textron 
Multi-engine Service Bulletin MEB-57-02, all dated December 20, 2017. 
As applicable, these service bulletins provide the manufacturer's 
optional procedures for installing access panels for easier access to 
the forward lower carry through spars. This AD does not require 
installing the access panels.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires repetitively inspecting the left and the right 
forward lower carry through spar cap for cracks and replacing the carry 
through spar if cracks are found. This AD also requires sending the 
inspection results to the FAA.

Interim Action

    We consider this AD interim action. Textron Aviation Inc. is 
evaluating the initial and repetitive inspection intervals, as well as 
designing a replacement lower carry through spar cap from an improved 
material. After the evaluations are complete and the design 
modification is developed, approved, and available, we may consider 
additional rulemaking.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule 
because cracks in the left and/or the right forward lower carry through 
spar cap could cause the carry through spar cap to fail during flight 
and result in loss of control. Therefore, we find good cause that 
notice and opportunity for prior public comment are impracticable. In 
addition, for the reason stated above, we find that good cause exists 
for making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number FAA-2018-
0068 and Product Identifier 2017-CE-049-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this final rule. We will 
consider all comments received by the closing date and may amend this 
final rule because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this final rule.

Costs of Compliance

    We estimate that this AD affects 2,147 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                            Cost per
            Action                   Labor cost          Parts cost         product      Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Inspect the left and the       12 work-hours x $85    Not applicable..  $1,020 per       $2,189,940 per
 right forward lower carry      per hour = $1,020                        inspection       inspection cycle.
 through spar cap for cracks    per inspection cycle.                    cycle.
 (without inspection access
 panels).
----------------------------------------------------------------------------------------------------------------


[[Page 6116]]

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace carry through spar.................  800 work-hours x $85 per hour =              $5,000         $73,000
                                              $68,000.
----------------------------------------------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW, Washington, DC 20591. ATTN: Information 
Collection Clearance Officer, AES-200.

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 small airplanes, gliders, 
balloons, airships, domestic business jet transport airplanes, and 
associated appliances to the Director of the Policy and Innovation 
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 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):

2018-03-03 Textron Aviation Inc.: Amendment 39-19176; Docket No. 
FAA-2018-0068; Product Identifier 2017-CE-049-AD.

(a) Effective Date

    This AD is effective February 28, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the following Textron Aviation Inc. (type 
certificate previously held by Cessna Aircraft Company) model 
airplanes, that are certificated in any category:

 Table 1 to Paragraph (c) of This AD--Affected Models and Serial Numbers
------------------------------------------------------------------------
                 Model                            Serial numbers
------------------------------------------------------------------------
401....................................  401-0001 through 401-0322
401A...................................  401A0001 through 401A0132
401B...................................  401B0001 through 401B0221
402....................................  402-0001 through 402-0322
402A...................................  402A0001 through 402A0129
402B...................................  402B0001 through 402B1384
402C...................................  689, 402C0001 through 402C1020
411....................................  411-0001 through 411-0250
411A...................................  411-0251 through 411-0300
414....................................  414-0001 through 414-0965
414A...................................  414A0001 through 414A1212
421....................................  421-0001 through 421-0200
421A...................................  421A0001 through 421A0158
421B...................................  421B0001 through 421B0970
421C...................................  421C0001 through 421C1807
425....................................  425-0001 through 425-0236
------------------------------------------------------------------------

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a report that a fully cracked lower 
forward carry through spar cap was found on a Textron Model 402C 
airplane. We are issuing this AD to prevent failure of the carry 
through spar cap during flight. The unsafe condition, if not 
addressed, could result in loss of control.

(f) Compliance

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

(g) Initial Inspection for All Affected Airplanes With 24,975 Hours 
Time-In-Service (TIS) or More on the Carry Through Spars

    Within the next 25 hours TIS after February 28, 2018 (the 
effective date of this

[[Page 6117]]

AD), do a detailed visual inspection of the left and right forward 
lower carry through spar cap for cracks. Using a 10X magnifier 
visually inspect the bottom surface of the carry through spar cap in 
the areas around the fasteners located just inboard of the left-hand 
and right-hand forward lower wing fittings. If a crack is not 
positively identified during the detailed visual inspection but is 
suspected or the area is questionable, before further flight, do a 
surface eddy current inspection of the suspected area. Do these 
inspections using the Accomplishment Instructions in Textron 
Aviation Multi-engine Mandatory Service Letter MEL-57-01 and Textron 
Aviation Conquest Mandatory Service Letter CQL-57-01, both dated 
December 18, 2017, as applicable.

(h) Initial Inspection for All Affected Airplanes With Less Than 24,975 
Hours TIS on the Carry Through Spars

    Using the compliance times listed in paragraphs (h)(1) through 
(3) of this AD, do a detailed visual inspection of the left and 
right forward lower carry through spar cap for cracks. Using a 10X 
magnifier visually inspect the bottom surface of the carry through 
spar cap in the areas around the fasteners located just inboard of 
the left-hand and right-hand forward lower wing fittings. If a crack 
is not positively identified during the detailed visual inspection 
but is suspected or the area is questionable, before further flight, 
do a surface eddy current inspection of the suspected area. Do these 
inspections using the Accomplishment Instructions in Textron 
Aviation Multi-engine Mandatory Service Letter MEL-57-01 and Textron 
Aviation Conquest Mandatory Service Letter CQL-57-01, both dated 
December 18, 2017, as applicable.
    (1) For Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 
411A, 414, 414A, 421, and 421A airplanes: Before the accumulation of 
15,000 TIS on the carry through spars or within the next 50 hours 
TIS after February 28, 2018 (the effective date of this AD), 
whichever occurs later.
    (2) For Models 421B and 421C airplanes: Before the accumulation 
of 12,000 hours TIS on the carry through spars or within the next 50 
hours TIS after February 28, 2018 (the effective date of this AD), 
whichever occurs later.
    (3) For Model 425 airplanes: Before the accumulation of 11,000 
TIS on the carry through spars or within the next 50 hours TIS after 
February 28, 2018 (the effective date of this AD), whichever occurs 
later.

(i) Repetitive Inspections for All Affected Airplanes

    If no cracks are found during the detailed visual inspections or 
the surface eddy current inspections required in paragraphs (g) and 
(h) of this AD, repetitively thereafter inspect at intervals not to 
exceed 50 hours TIS. Inspect as specified in paragraphs (g) and (h) 
of this AD using the service information specified in each paragraph 
as applicable.

(j) Replacement of Carry Through Spars for All Affected Airplanes

    If cracks are found during any inspection required in paragraphs 
(g) through (i) and paragraph (k) of this AD, before further flight, 
replace the carry through spar.

(k) Initial and Repetitive Inspections of Newly Replaced Carry Through 
Spars for All Affected Airplanes

    At the compliance times in paragraphs (k)(1) through (3) of this 
AD, do a detailed visual inspection of the left and right forward 
lower carry through spar cap for cracks. Using a 10X magnifier 
visually inspect the bottom surface of the carry through spar cap in 
the areas around the fasteners located just inboard of the left-hand 
and right-hand forward lower wing fittings. If a crack is not 
positively identified during the detailed visual inspection but is 
suspected or the area is questionable, before further flight, do a 
surface eddy current inspection of the suspected area. Do these 
inspections using the Accomplishment Instructions in Textron 
Aviation Multi-engine Mandatory Service Letter MEL-57-01 and Textron 
Aviation Conquest Mandatory Service Letter CQL-57-01, both dated 
December 18, 2017, as applicable.
    (1) For Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 
411A, 414, 414A, 421, and 421A airplanes: Before the accumulation of 
15,000 hours TIS on the newly installed carry through spar. If no 
cracks are found, repetitively thereafter inspect at intervals not 
to exceed 50 hours TIS.
    (2) For Models 421B and 421C airplanes: Before the accumulation 
of 12,000 hours TIS on the newly installed carry through spar. If no 
cracks are found, repetitively thereafter inspect at intervals not 
to exceed 50 hours TIS.
    (3) For Model 425 airplanes: Before the accumulation of 11,000 
hours TIS on the newly installed carry through spar. If no cracks 
are found, repetitively thereafter inspect at intervals not to 
exceed 50 hours TIS.

(l) Reporting Requirement for All Affected Airplanes

    Within 30 days after each inspection required by paragraphs (g) 
through (i) and paragraph (k) of this AD, report the results of the 
inspection to the FAA representative identified in paragraph (q) of 
this AD using the undated Attachment (titled Spar Cap Inspection 
Results Form and Spar Cap Inspection Results Form Continued) to 
Textron Aviation Multi-engine Mandatory Service Letter MEL-57-01 and 
Textron Aviation Conquest Mandatory Service Letter CQL-57-01, both 
dated December 18, 2017, as applicable. Please identify AD 2018-03-
03 in the subject line if submitted through email.

(m) Installation of Optional Access Panels All Affected Airplanes

    Textron Aviation Conquest Service Bulletin CQB-57-01, Textron 
Aviation Multi-engine Service Bulletin MEB-57-01, and Textron Multi-
engine Service Bulletin MEB-57-02, all dated December 20, 2017, 
provide the manufacturer's optional procedures for installing access 
panels for easier access to the forward carry through spars. This AD 
does not require installing the access panels, but does not restrict 
the owner/operator from doing so.

(n) Credit for Actions Done Following Previous Service Information for 
Affected Airplanes

    This AD allows credit for the initial inspection of the forward 
lower carry through spar cap required in paragraphs (g) and (h) of 
this AD if done before February 28, 2018 (the effective date of this 
AD) using the following documents:
    (1) Models 401, 401A, 401B, 402, 402A, 402B airplanes: Cessna 
Aircraft Company Model 401/402 Supplemental Inspection Document, 
Supplemental Inspection Number 57-10-10, dated June 3, 2002.
    (2) Model 402C airplanes: Cessna Aircraft Company Model 402C 
Maintenance Manual, Supplemental Inspection Number 57-10-14, dated 
June 3, 2002.
    (3) Models 411 and 411A airplanes: Cessna Aircraft Company Model 
411, Supplemental Inspection Document, Supplemental Inspection 
Number 57-10-10, dated January 6, 2003.
    (4) Model 414 airplanes: Cessna Aircraft Company Model 414 
Supplemental Inspection Document, Supplemental Inspection Number 57-
10-10, dated August 1, 2002.
    (5) Model 414A airplanes: Cessna Aircraft Company Model 414A 
Supplemental Inspection Document, Supplemental Inspection Number 57-
10-14, dated August 1, 2002.
    (6) Models 421, 421A, and 421B airplanes: Cessna Aircraft 
Company Model 421 Supplemental Inspection Document, Supplemental 
Inspection Number 57-10-10, dated March 3, 2003.
    (7) Model 421C airplanes: Cessna Aircraft Company Model 421C 
Supplemental Inspection Document, Supplemental Inspection Number 57-
10-14, dated January 6, 2003.

(o) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 15 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(p) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Wichita ACO 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

[[Page 6118]]

principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
certification office, send it to the attention of the person 
identified in paragraph (q) of this AD.
    (2) 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.

(q) Related Information

    For more information about this AD, contact Bobbie Kroetch, 
Aerospace Engineer, Wichita ACO Branch, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; telephone: (316) 946-4155; fax: (316) 946-
4107; email: [email protected] or [email protected].

(r) 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) Textron Aviation Multi-engine Mandatory Service Letter MEL-
57-01, dated December 18, 2017 (includes the undated Attachment 
titled Spar Cap Inspection Results Form and Spar Cap Inspection 
Results Form Continued).
    (ii) Textron Aviation Conquest Mandatory Service Letter CQL-57-
01, dated December 18, 2017 (includes the undated Attachment titled 
Spar Cap Inspection Results Form and Spar Cap Inspection Results 
Form Continued).
    (3) For Textron Aviation service information identified in this 
AD, contact Textron Aviation Inc., Textron Aviation Customer 
Service, One Cessna Blvd., Wichita, Kansas 67215; telephone: (316) 
517-5800; email: [email protected]; internet: www.txtav.com.
    (4) You may view this service information at FAA, Policy and 
Innovation Division, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on February 2, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division, Aircraft Certification 
Service.
[FR Doc. 2018-02551 Filed 2-12-18; 8:45 am]
BILLING CODE 4910-13-P