Airworthiness Directives; Textron Aviation Inc. Airplanes, 4605-4609 [2018-01923]

Download as PDF 4605 Proposed Rules Federal Register Vol. 83, No. 22 Thursday, February 1, 2018 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0049; Product Identifier 2017–CE–031–AD] RIN 2120–AA64 Examining the AD Docket Airworthiness Directives; Textron Aviation Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Textron Aviation Inc. Models 172N, 172P, 172Q, 172RG, F172N, F172P, FR172K, R172K, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, T182, F182P, F182Q, F182RG, R182, TR182, 206, P206/ TP206, U206/TU206, 207/T207, 210–5 (205), 210–5A (205A), 210B, 210C, 210D, 210E, 210F, and T210F airplanes. This proposed AD was prompted by a report of cracks found in the lower area of the forward cabin doorpost bulkhead. This proposed AD would require repetitively inspecting the lower forward doorpost at the strut attach fitting for cracks and making all necessary repairs. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by March 19, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://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. daltland on DSKBBV9HB2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:25 Jan 31, 2018 Jkt 244001 • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact 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. You may review 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. You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0049; 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 NPRM, 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0049; Product Identifier 2017–CE– 031–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion We received a report from an operator of one of the affected Textron Aviation Inc. model airplanes that cracks were found in the lower area of the forward cabin doorpost bulkhead. Further investigation revealed more than four dozen similar cracks on Textron Aviation Inc. 100 and 200 airplanes. It has been determined that the cracks result from metal fatigue. This condition, if not detected and addressed, could result in failure of the wing strut attach point during operation, which could result in loss of control. Related Service Information Under 1 CFR Part 51 We reviewed Cessna Single Engine Accomplishment Instructions SEB95– 19, dated December 29, 1995; and Cessna Single-Engine Accomplishment Instructions SEB93–5R1, Revision 1, dated September 8, 1995. As applicable, the service information describes procedures for repetitively inspecting the lower area of the forward cabin doorposts for cracks and repairing any cracks found by modifying the area with the applicable Cessna service kit. 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 Cessna Single Engine Service Bulletin SEB93–5, Revision 1, dated September 8, 1995, and Cessna Single Engine Service Bulletin SEB95– 19, dated December 29, 1995. As applicable, these service bulletins provide the manufacturer’s recommended compliance times for the initial and repetitive inspections. These service bulletins also specify a terminating action for the repetitive inspections when the applicable Cessna repair service kit is installed if cracks are found. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or E:\FR\FM\01FEP1.SGM 01FEP1 4606 Federal Register / Vol. 83, No. 22 / Thursday, February 1, 2018 / Proposed Rules develop in other products of the same type design. Proposed AD Requirements This proposed AD would require repetitively inspecting the lower area of the forward cabin doorposts for cracks and repairing any cracks found by modifying the area with the applicable Cessna service kit. Costs of Compliance We estimate that this proposed AD affects 14,653 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Cost per product Action Labor cost Parts cost Inspect the lower area of the forward cabin doorposts for cracks. 1.5 work-hours × $85 per hour = $127.50 Not applicable ......... We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspection. We have no way of $127.50 Cost on U.S. operators $1,868,257.50 determining the number of aircraft that might need this repair: ON-CONDITION COSTS Action daltland on DSKBBV9HB2PROD with PROPOSALS Install Install Install Install Install Cessna Cessna Cessna Cessna Cessna Single-Engine Single-Engine Single-Engine Single-Engine Single-Engine Labor cost Service Service Service Service Service Kit Kit Kit Kit Kit SK172–147 SK182–115 SK206–42C SK207–19 ... SK210–156 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, VerDate Sep<11>2014 16:25 Jan 31, 2018 Jkt 244001 24 24 24 24 24 work-hours work-hours work-hours work-hours work-hours × × × × × $85 $85 $85 $85 $85 per per per per per hour hour hour hour hour = = = = = Parts cost $2,040 $2,040 $2,040 $2,040 $2,040 balloons, airships, domestic business jet transport airplanes, and associated appliances to the Director of the Policy and Innovation Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 ...................... ...................... ...................... ...................... ...................... $646 920 500 587 952 Cost per product $2,686 2,960 2,540 2,627 2,992 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Textron Aviation Inc.: Docket No. FAA– 2017–0049; Product Identifier 2017–CE– 031–AD. (a) Comments Due Date We must receive comments by March 19, 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: BILLING CODE 4910–13–P E:\FR\FM\01FEP1.SGM 01FEP1 Federal Register / Vol. 83, No. 22 / Thursday, February 1, 2018 / Proposed Rules 4607 Table 1 to paragraph (c) of this AD - Affected Models and Serial Numbers Model 172RG Fl72N Fl72P FR172K Rl72K 182E 182F 182G 182H 182J 182K 182L 182M 182N 182P 182Q daltland on DSKBBV9HB2PROD with PROPOSALS 182R 182R/Tl82 Fl82P Fl82Q Fl82RG Rl82 Rl82/TR182 206 P206/TP206 U206/TU206 VerDate Sep<11>2014 16:25 Jan 31, 2018 Serial N urn hers 17272885 through 17274009 17274010 through 17276654 17275869, 17275927 through 17275934, 17275952, 17275959, 17275960, 17275962, 17275964, 17275965, 17275967,17275968,17275969,17275971, 17275992, 17275999,17276002, 17276005, 17276029, 17276032, 17276042, 17276045, 17276051, 17276052, 17276054, 17276101,17276109, 17276140,17276147, 17276188,and 17276211 691, 172RGOOO 1 through 172RG 1191 Fl7201910 through Fl7202039 F 17202040 through F 17202254 FR17200656 through FR17200675 Rl723200 through Rl723454 18253599 through 18254423 18254424 through 18255058 18255059 through 18255844 634 and 18255846 through 18256684 18256685 through 18257625 18255845, 18257626 through 18257698, and 18257700 through 18258505 18258506 through 18259305 18257699 and 18259306 through 18260055 18260056 through 18260825 675, 18260826 through 18263478, and 18263480 through 18265175 18263479, 18265176 through 18267301, and 18267303 through 18267715 18268542 through 18268586 18267302 and 18267716 through 18268541 F 18200001 through F 18200025 F 18200026 through F 18200169 FR1820000lthrough FR18200070 Rl8200002 through Rl8200583 Rl8200001 and Rl8200584 through Rl8202039 206-0001 through 206-0275 P206-000 1 through P206-0603 and P20600604 through P2060064 7 676, U206-0276 through U206-1444, and U20601445 through U20607020 Jkt 244001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4725 E:\FR\FM\01FEP1.SGM 01FEP1 EP01FE18.000</GPH> 172N 172P 172Q Federal Register / Vol. 83, No. 22 / Thursday, February 1, 2018 / Proposed Rules BILLING CODE 4910–13–C (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 of cracks found in the lower area of the forward cabin doorpost bulkhead. We are issuing this AD to detect and address cracking of the wing strut attach point. The unsafe condition, if not addressed, could result in failure of the wing in operation, which could result in loss of control. daltland on DSKBBV9HB2PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections At the following compliance times, visually inspect the lower forward doorpost at the strut attach fitting for cracks. Do the inspection following Cessna Single Engine Accomplishment Instructions SEB95–19, dated December 29, 1995, and Cessna SingleEngine Accomplishment Instructions SEB93– 5R1, dated September 8, 1995, as applicable. During the inspection, pay special attention to the contour of the wing strut support fitting. If cracks are present, they should be visible at the intersection of the doorpost and the forward doorpost bulkhead. (1) As of the effective date of this AD, airplanes that have accumulated less than 4,000 hours time-in-service (TIS): Initially inspect upon reaching 4,000 hours TIS or within the next 200 hours TIS after the effective date of this AD, whichever occurs later. (2) As of the effective date of this AD, airplanes that have accumulated 4,000 hours TIS or more: Initially inspect within the next 200 hours TIS after the effective date of this AD or within the next 12 months after the effective date of this AD, whichever occurs first. (h) Repair Cracks If cracks are found during any inspection required in paragraph (g) or paragraph (i) of this AD, before further flight, install the applicable service kit as specified in Cessna Single Engine Accomplishment Instructions SEB95–19, dated December 29, 1995, and Cessna Single-Engine Accomplishment VerDate Sep<11>2014 16:25 Jan 31, 2018 Jkt 244001 Instructions SEB93–5R1, dated September 8, 1995, as applicable. (i) Repetitive Inspections (1) If no cracks are found during the initial inspection required in paragraph (g) of this AD, repetitively thereafter inspect every 12 months or 1,000 hours TIS, whichever occurs first, as long as no cracks are found. Do the inspections following the applicable service information specified in paragraph (g) of this AD. (2) If cracks were found during any inspection required in paragraph (g) or paragraph (i)(1) of this AD, repetitively thereafter inspect at intervals not to exceed 1,000 hours TIS after installing the applicable service kit. These repetitive inspections should be done following the applicable Accomplishment Instructions of the service information specified in paragraph (g) of this AD to the fullest extent while additionally looking for cracks extending beyond the added repair parts. (j) Contacting the Manufacturer If cracks are found that extend beyond the service kit doublers that were installed as required in paragraph (h) of this AD during any inspection required in paragraph (i)(2) of this AD, before further flight, contact the manufacturer at the address specified in paragraph (m)(2) of this AD for an FAAapproved repair scheme designed specifically for this AD and incorporate that repair. (k) Credit for Previous Actions (1) For the following Textron Aviation Inc. model airplanes, credit will be given for the initial inspection required by paragraph (g) of this AD if done before the effective date of this AD following the Accomplishment Instructions in Cessna Single Engine Service Bulletin SEB93–5, dated March 26, 1993. (i) Model 210–5 (205) airplanes, serial numbers (S/N) 205–0551 and 205–0556 through 205–0577. (ii) Model 206 airplanes, S/N 206–0094 and 206–0138 through 206–0275. (iii) Model P206/TP206 airplanes, S/N P206–0001 through P206–0603 and P20600604 through P20600647. (iv) Model U206/TU206 airplanes, S/N 676, U206–0276 through U206–1444, and U20601445 through U20607020. (v) Model 207/T207 airplanes, S/N 20700001 through 20700788. (2) For Textron Aviation Inc. Model U206/ TU206 airplanes, S/N 676, U206–0276 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 through U206–1444, and U20601445 through U20607020: Credit will be given for the repair required in paragraph (h) of this AD if done before the effective date of this AD following the Accomplishment Instructions in Cessna Single Engine Service Bulletin SEB93–5, dated March 26, 1993. (3) For Textron Aviation Inc. Model 207/ T207 airplanes, S/N 20700001 through 20700788: No credit will be given for the repair required in paragraph (h) of this AD if done before the effective date of this AD following the Accomplishment Instructions in Cessna Single Engine Service Bulletin SEB93–5, dated March 26, 1993. (l) 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 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 (m) 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. (m) Related Information (1) 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. (2) For 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. You may review 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. E:\FR\FM\01FEP1.SGM 01FEP1 EP01FE18.001</GPH> 4608 4609 Federal Register / Vol. 83, No. 22 / Thursday, February 1, 2018 / Proposed Rules Issued in Kansas City, Missouri, on January 24, 2018. Pat Mullen, Acting Deputy Director, Policy & Innovation Division, Aircraft Certification Service. [FR Doc. 2018–01923 Filed 1–31–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2017–1118; Product Identifier 2017–NE–40–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Corporation Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) model 250–C turboshaft engines. This proposed AD was prompted by several reports of engine power loss, one of which resulted in a fatal helicopter accident. This proposed AD would require removal of the bearing assembly, part number (P/N) 2544198, in the power turbine governor (PTG) and its replacement with a bearing assembly eligible for installation. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by March 19, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: daltland on DSKBBV9HB2PROD with PROPOSALS For service information identified in this NPRM, contact Rolls-Royce Corporation, 450 South Meridian Street, Mail Code NB–02–05, Indianapolis, IN 46225; phone: 317–230–3774; email: indy.pubs.services@rolls-royce.com; internet: www.rolls-royce.com. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7759. You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 1118; 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 NPRM, 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: John Tallarovic, Aerospace Engineer, Chicago ACO Branch, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; phone: 847–294– 8180; fax: 847–294–7834; email: john.tallarovic@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–1118; Product Identifier 2017– NE–40–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion We were prompted to issue this NPRM based upon several reports of loss of engine power on certain RRC model 250–C turboshaft engines installed on single-engine helicopters. One of these instances of power loss resulted in a fatal helicopter accident on May 4, 2016. During the course of the investigation of the 2016 fatal accident, RRC determined that the root cause of this engine power loss was the failure of the bearing assembly, P/N 2544198, in the PTG, due to lack of lubrication. Although RRC had issued a service bulletin in 2009 to address the failure of this bearing assembly, our risk assessment had not supported issuance of an AD at that time. Based on more recent service experience, and the fatal accident in 2016, we are now proposing an AD to remove the affected bearing assembly in the PTG and replace it with a bearing assembly with a new design. This condition, if not addressed, could result in failure of the PTG, failure of the engine, in-flight shutdown, and forced autorotation landing or accident. Related Service Information We reviewed Rolls-Royce Corporation Commercial Engine Bulletin (CEB) 1402, Revision 2, dated February 4, 2009. The CEB provides guidance on replacing the P/N 2544198 bearing assembly in the PTG with a bearing assembly eligible for installation. FAA’s Determination We are proposing 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. Proposed AD Requirements This proposed AD would require removal of the affected bearing assembly in the PTG and its replacement with a bearing assembly eligible for installation. Costs of Compliance We estimate that this proposed AD affects 2,928 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Remove and replace PTG bearing assembly 8 work-hours × $85 per hour = $680 ............. VerDate Sep<11>2014 16:25 Jan 31, 2018 Jkt 244001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Parts cost E:\FR\FM\01FEP1.SGM $1,700 01FEP1 Cost per product $2,380 Cost on U.S. operators $6,968,640

Agencies

[Federal Register Volume 83, Number 22 (Thursday, February 1, 2018)]
[Proposed Rules]
[Pages 4605-4609]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-01923]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 83, No. 22 / Thursday, February 1, 2018 / 
Proposed Rules

[[Page 4605]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0049; Product Identifier 2017-CE-031-AD]
RIN 2120-AA64


Airworthiness Directives; Textron Aviation Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Textron Aviation Inc. Models 172N, 172P, 172Q, 172RG, F172N, 
F172P, FR172K, R172K, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 
182N, 182P, 182Q, 182R, T182, F182P, F182Q, F182RG, R182, TR182, 206, 
P206/TP206, U206/TU206, 207/T207, 210-5 (205), 210-5A (205A), 210B, 
210C, 210D, 210E, 210F, and T210F airplanes. This proposed AD was 
prompted by a report of cracks found in the lower area of the forward 
cabin doorpost bulkhead. This proposed AD would require repetitively 
inspecting the lower forward doorpost at the strut attach fitting for 
cracks and making all necessary repairs. We are proposing this AD to 
address the unsafe condition on these products.

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

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Textron 
Aviation Inc., Textron Aviation Customer Service, One Cessna Blvd., 
Wichita, Kansas 67215; telephone: (316) 517-5800; email: 
[email protected]; internet: www.txtav.com. You may review 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.

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-2017-
0049; 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 NPRM, 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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0049; 
Product Identifier 2017-CE-031-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM because 
of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    We received a report from an operator of one of the affected 
Textron Aviation Inc. model airplanes that cracks were found in the 
lower area of the forward cabin doorpost bulkhead. Further 
investigation revealed more than four dozen similar cracks on Textron 
Aviation Inc. 100 and 200 airplanes. It has been determined that the 
cracks result from metal fatigue.
    This condition, if not detected and addressed, could result in 
failure of the wing strut attach point during operation, which could 
result in loss of control.

Related Service Information Under 1 CFR Part 51

    We reviewed Cessna Single Engine Accomplishment Instructions SEB95-
19, dated December 29, 1995; and Cessna Single-Engine Accomplishment 
Instructions SEB93-5R1, Revision 1, dated September 8, 1995. As 
applicable, the service information describes procedures for 
repetitively inspecting the lower area of the forward cabin doorposts 
for cracks and repairing any cracks found by modifying the area with 
the applicable Cessna service kit. 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 Cessna Single Engine Service Bulletin SEB93-5, Revision 
1, dated September 8, 1995, and Cessna Single Engine Service Bulletin 
SEB95-19, dated December 29, 1995. As applicable, these service 
bulletins provide the manufacturer's recommended compliance times for 
the initial and repetitive inspections.
    These service bulletins also specify a terminating action for the 
repetitive inspections when the applicable Cessna repair service kit is 
installed if cracks are found.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or

[[Page 4606]]

develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require repetitively inspecting the lower 
area of the forward cabin doorposts for cracks and repairing any cracks 
found by modifying the area with the applicable Cessna service kit.

Costs of Compliance

    We estimate that this proposed AD affects 14,653 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
              Action                      Labor cost              Parts cost          product        operators
----------------------------------------------------------------------------------------------------------------
Inspect the lower area of the      1.5 work-hours x $85 per  Not applicable.....         $127.50   $1,868,257.50
 forward cabin doorposts for        hour = $127.50.
 cracks.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Install Cessna Single-Engine Service Kit     24 work-hours x $85 per hour =                 $646          $2,686
 SK172-147.                                   $2,040.
Install Cessna Single-Engine Service Kit     24 work-hours x $85 per hour =                  920           2,960
 SK182-115.                                   $2,040.
Install Cessna Single-Engine Service Kit     24 work-hours x $85 per hour =                  500           2,540
 SK206-42C.                                   $2,040.
Install Cessna Single-Engine Service Kit     24 work-hours x $85 per hour =                  587           2,627
 SK207-19.                                    $2,040.
Install Cessna Single-Engine Service Kit     24 work-hours x $85 per hour =                  952           2,992
 SK210-156.                                   $2,040.
----------------------------------------------------------------------------------------------------------------

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

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Textron Aviation Inc.: Docket No. FAA-2017-0049; Product Identifier 
2017-CE-031-AD.

(a) Comments Due Date

    We must receive comments by March 19, 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:
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(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 of cracks found in the lower 
area of the forward cabin doorpost bulkhead. We are issuing this AD 
to detect and address cracking of the wing strut attach point. The 
unsafe condition, if not addressed, could result in failure of the 
wing in operation, which could result in loss of control.

(f) Compliance

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

(g) Inspections

    At the following compliance times, visually inspect the lower 
forward doorpost at the strut attach fitting for cracks. Do the 
inspection following Cessna Single Engine Accomplishment 
Instructions SEB95-19, dated December 29, 1995, and Cessna Single-
Engine Accomplishment Instructions SEB93-5R1, dated September 8, 
1995, as applicable. During the inspection, pay special attention to 
the contour of the wing strut support fitting. If cracks are 
present, they should be visible at the intersection of the doorpost 
and the forward doorpost bulkhead.
    (1) As of the effective date of this AD, airplanes that have 
accumulated less than 4,000 hours time-in-service (TIS): Initially 
inspect upon reaching 4,000 hours TIS or within the next 200 hours 
TIS after the effective date of this AD, whichever occurs later.
    (2) As of the effective date of this AD, airplanes that have 
accumulated 4,000 hours TIS or more: Initially inspect within the 
next 200 hours TIS after the effective date of this AD or within the 
next 12 months after the effective date of this AD, whichever occurs 
first.

(h) Repair Cracks

    If cracks are found during any inspection required in paragraph 
(g) or paragraph (i) of this AD, before further flight, install the 
applicable service kit as specified in Cessna Single Engine 
Accomplishment Instructions SEB95-19, dated December 29, 1995, and 
Cessna Single-Engine Accomplishment Instructions SEB93-5R1, dated 
September 8, 1995, as applicable.

(i) Repetitive Inspections

    (1) If no cracks are found during the initial inspection 
required in paragraph (g) of this AD, repetitively thereafter 
inspect every 12 months or 1,000 hours TIS, whichever occurs first, 
as long as no cracks are found. Do the inspections following the 
applicable service information specified in paragraph (g) of this 
AD.
    (2) If cracks were found during any inspection required in 
paragraph (g) or paragraph (i)(1) of this AD, repetitively 
thereafter inspect at intervals not to exceed 1,000 hours TIS after 
installing the applicable service kit. These repetitive inspections 
should be done following the applicable Accomplishment Instructions 
of the service information specified in paragraph (g) of this AD to 
the fullest extent while additionally looking for cracks extending 
beyond the added repair parts.

(j) Contacting the Manufacturer

    If cracks are found that extend beyond the service kit doublers 
that were installed as required in paragraph (h) of this AD during 
any inspection required in paragraph (i)(2) of this AD, before 
further flight, contact the manufacturer at the address specified in 
paragraph (m)(2) of this AD for an FAA-approved repair scheme 
designed specifically for this AD and incorporate that repair.

(k) Credit for Previous Actions

    (1) For the following Textron Aviation Inc. model airplanes, 
credit will be given for the initial inspection required by 
paragraph (g) of this AD if done before the effective date of this 
AD following the Accomplishment Instructions in Cessna Single Engine 
Service Bulletin SEB93-5, dated March 26, 1993.
    (i) Model 210-5 (205) airplanes, serial numbers (S/N) 205-0551 
and 205-0556 through 205-0577.
    (ii) Model 206 airplanes, S/N 206-0094 and 206-0138 through 206-
0275.
    (iii) Model P206/TP206 airplanes, S/N P206-0001 through P206-
0603 and P20600604 through P20600647.
    (iv) Model U206/TU206 airplanes, S/N 676, U206-0276 through 
U206-1444, and U20601445 through U20607020.
    (v) Model 207/T207 airplanes, S/N 20700001 through 20700788.
    (2) For Textron Aviation Inc. Model U206/TU206 airplanes, S/N 
676, U206-0276 through U206-1444, and U20601445 through U20607020: 
Credit will be given for the repair required in paragraph (h) of 
this AD if done before the effective date of this AD following the 
Accomplishment Instructions in Cessna Single Engine Service Bulletin 
SEB93-5, dated March 26, 1993.
    (3) For Textron Aviation Inc. Model 207/T207 airplanes, S/N 
20700001 through 20700788: No credit will be given for the repair 
required in paragraph (h) of this AD if done before the effective 
date of this AD following the Accomplishment Instructions in Cessna 
Single Engine Service Bulletin SEB93-5, dated March 26, 1993.

(l) 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 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 (m) 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.

(m) Related Information

    (1) 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].
    (2) For 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. You may review 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.


[[Page 4609]]


    Issued in Kansas City, Missouri, on January 24, 2018.
Pat Mullen,
Acting Deputy Director, Policy & Innovation Division, Aircraft 
Certification Service.
[FR Doc. 2018-01923 Filed 1-31-18; 8:45 am]
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