Airworthiness Directives; Textron Aviation Inc. (Textron) Airplanes, 59457-59460 [2020-20681]

Download as PDF Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Proposed Rules (a) Comments Due Date The FAA must receive comments by November 6, 2020. (b) Affected ADs This AD replaces AD 2014–12–12, Amendment 39–17873 (79 FR 36638, June 30, 2014) (‘‘AD 2014–12–12’’). (c) Applicability This AD applies to Airbus Helicopters Model EC120B and EC130B4 helicopters, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2020–0095, dated April 29, 2020 (‘‘EASA AD 2020–0095’’). (d) Subject Joint Aircraft System Component (JASC) Code 5200, Doors. (e) Reason This AD was prompted by reports of passengers not being able to open a helicopter’s left-hand door after landing. The FAA is issuing this AD to address failure of the sliding door star support, which could inhibit the operation of the sliding door from the inside, delaying the evacuation of passengers during an emergency. (j) Related Information (1) For information about EASA AD 2020– 0095, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@ easa.europa.eu; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https:// ad.easa.europa.eu. You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call 817–222–5110. This material may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–3343. (2) For more information about this AD, contact David Hatfield, Aviation Safety Engineer, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5485; email david.hatfield@faa.gov. Federal Aviation Administration 14 CFR Part 39 Examining the AD Docket Issued on September 15, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–20718 Filed 9–21–20; 8:45 am] BILLING CODE 4910–13–P Comply with this AD within the compliance times specified, unless already done. DEPARTMENT OF TRANSPORTATION (h) Exceptions to EASA AD 2020–0095 (1) Where EASA AD 2020–0095 refers to its effective date, this AD requires using the effective date of this AD. (2) Where paragraph (1) of EASA AD 2020– 0095 specifies to complete the actions within 24 months after its effective date, this AD requires completion within 460 hours timein-service after the effective date of this AD. (3) The ‘‘Remarks’’ section of EASA AD 2020–0095 does not apply to this AD. (4) Although the service information referenced in EASA AD 2020–0095 specifies to discard certain parts, this AD does not include that requirement. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: David Hatfield, Aviation Safety Engineer, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5116; email 9-ASW-FTW-AMOCRequests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, notify your principal inspector or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. VerDate Sep<11>2014 17:17 Sep 21, 2020 Jkt 250001 The FAA must receive comments on this proposed AD by November 6, 2020. DATES: 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., One Cessna Boulevard, Wichita, KS 67215: Telephone: 316–517–5800: email: teamturbopropsupport@ txtav.com; internet: https:// support.cessna.com. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust St., Kansas City, MO 64106. For information on the availability of this material at the FAA, call 816–329–4148. (f) Compliance (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2020–0095. 59457 [Docket No. FAA–2020–0811; Product Identifier 2019–CE–055–AD] RIN 2120–AA64 Airworthiness Directives; Textron Aviation Inc. (Textron) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Textron (type certificate previously held by Cessna Aircraft Company) Models 208 and 208B airplanes. This proposed AD was prompted by reports of loose elevator torque tube attach fasteners. This proposed AD would require repetitively inspecting the inboard and outboard elevator torque tube attachments for loose or incorrectly installed fasteners, replacing all fasteners if loose or incorrectly installed fasteners are found, and reporting the inspection results to the FAA. This AD also includes optional actions to terminate the repetitive inspections. The FAA is proposing this AD to address the unsafe condition on these products. SUMMARY: PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 ADDRESSES: You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0811; 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 is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Bobbie Kroetch, Aerospace Engineer, Wichita ACO Branch, FAA, 1801 Airport Road, Wichita, Kansas 67209; phone: 316–946–4155; fax: 316–946– 4107; email: bobbie.kroetch@faa.gov or Wichita-COS@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites 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–2020–0811; Product Identifier 2019–CE–055–AD’’ at the beginning of your comments. The FAA will consider all comments received by E:\FR\FM\22SEP1.SGM 22SEP1 59458 Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Proposed Rules the closing date and may amend this NPRM because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact it receives about this proposed AD. airplanes. Textron identified a quality escape affecting certain serial-numbered Model 208 and 208B airplanes. Fastener holes in the inboard and outboard elevator torque tube connections may have been oversized and fasteners at the inboard and outboard torque tube connections may have been installed incorrectly. This condition, if not addressed, could result in failure of the elevator torque tube fasteners, leading to loss of elevator control and loss of controlled flight. Confidential Business Information Related Service Information Under 1 CFR Part 51 The FAA reviewed Task 27–30–00– 290, Left and Right Elevator Torque Tube Attach Points (Borescope) Special Detailed Inspection, dated October 1, 2018, of the Cessna Model 208 Maintenance Manual (Task 27–30–00– 290). This service information contains procedures for performing a detailed borescope inspection of the left and right elevator torque tube attach points. 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. Confidential Business Information (CBI) is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Bobbie Kroetch, Aerospace Engineer, Wichita ACO Branch, FAA, 1801 Airport Road, Wichita, Kansas 67209. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Discussion The FAA received reports of loose elevator torque tube attach fasteners on low flight time Textron Model 208B Other Related Service Information The FAA also reviewed Textron Aviation Mandatory Caravan Service Bulletin CAB–27–06, dated October 14, 2019 (CAB–27–06). This service information contains instructions for visually inspecting the left and right elevator torque tube attach points for the presence of loose rivets and replacing loose or incorrectly installed rivets. FAA’s Determination The FAA is proposing this AD because it evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of this same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ This proposed AD also requires reporting the inspection results to the FAA. Differences Between This Proposed AD and the Service Information Task 27–30–00–290 only specifies replacing loose fasteners. The proposed AD would require replacement of all 48 fasteners if any single inboard or outboard elevator torque tube attach fastener is found loose or incorrectly installed. The FAA determined based on field evidence that identification of one loose fastener often indicates other fasteners may be affected. CAB–27–06, which would not be incorporated by reference in this proposed AD, specifies performing an initial inspection within 800 flight hours or 12 months from date of receipt, whichever occurs first. This proposed AD would require an initial inspection before the airplane accumulates 800 hours time-in-service (TIS) or within 200 hours TIS after the AD effectivity date, whichever occurs later. CAB–27–06 also specifies, without sufficient data, that an inspection is not required for airplanes that have reached 4,000 hours. The FAA determined an inspection of high-time airplanes is necessary to verify whether these airplanes are affected. This proposed AD would require a one-time visual inspection for airplanes that have already accumulated 4,000 hours TIS. Costs of Compliance The FAA estimates that this proposed AD affects 232 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Inspection ....................... 1 work-hour × $85 per hour = $85 ... Not applicable ............... $85 per inspection cycle Reporting Requirement .. 1 work-hour × $85 per hour = $85 ... Not applicable ............... $85 per report ............... The FAA estimates the following costs to do any necessary replacements that would be required based on the VerDate Sep<11>2014 17:17 Sep 21, 2020 Jkt 250001 results of the proposed inspection. The FAA has no way of determining the PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Cost on U.S. operators $19,720 per inspection cycle. $19,720 per report. number of airplanes that might need these replacements: E:\FR\FM\22SEP1.SGM 22SEP1 Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Proposed Rules 59459 ON-CONDITION COSTS Action Labor cost Fastener Replacement: All 48 Fasteners ..................... 16 work-hours × $85 per hour = $1,360 ...................... According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. The FAA does not control warranty coverage for affected individuals. As a result, the FAA has included all costs in this cost estimate. 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 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 currently 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 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177–1524. 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. The FAA is 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 VerDate Sep<11>2014 17:17 Sep 21, 2020 Jkt 250001 that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings The FAA 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) Will not affect intrastate aviation in Alaska, and (3) 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 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. (Type Certificate Previously Held by Cessna Aircraft Company): Docket No. FAA–2020–0811; Product Identifier 2019–CE–055–AD. (a) Comments Due Date The FAA must receive comments by November 6, 2020. (b) Affected ADs None. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 Parts cost $10 Cost per product $1,370. (c) Applicability This AD applies to Textron Aviation Inc. (Textron) (type certificate previously held by Cessna Aircraft Company) Model 208 airplanes, serial numbers 20800564 through 20800594 and 20800603 through 20800605; and Model 208B airplanes, serial numbers 208B5141 through 208B5285, 208B5287 through 208B5305, 208B5307 through 208B5312, 208B5314, 208B5316 through 208B5344, 208B5346 through 208B5350, 208B5353, 208B5354, 208B5356 through 208B5359, 208B5362 through 208B5366, 208B5401, 208B5403, 208B5404, and 208B5408; certificated in any category. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code: 5520, Elevator Structure. (e) Unsafe Condition This AD was prompted by reports loose elevator torque tube attach fasteners. The FAA is issuing this AD to detect and correct loosening and eventual failure of the elevator torque tube attach fasteners. The unsafe condition, if not addressed, could result in loss of elevator control, resulting in loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Fastener Replacement (1) At the following compliance times, inspect each inboard and outboard elevator torque tube attach fastener for looseness and fretting by following sections 2.C. and 2.D. of Task 27–30–00–290, Left and Right Elevator Torque Tube Attach Points (Borescope) Special Detailed Inspection, dated October 1, 2018, of the Cessna Model 208 Maintenance Manual. You must also inspect for incorrectly installed fasteners. (i) For airplanes that have accumulated less than 800 hours time-in-service (TIS) as of the effective date of this AD, complete the initial inspection before the airplane accumulates 800 hours TIS or within 200 hours TIS after the effective date of the AD, whichever occurs later. Thereafter, repeat the visual inspection at intervals not to exceed 200 hours TIS until the airplane has accumulated 4,000 hours TIS or until all 48 elevator torque tube attach fasteners are replaced, whichever occurs first. (ii) For airplanes that have accumulated 800 or more hours TIS but less than 4,000 hours TIS as of the effective date of this AD, complete the initial inspection within 200 hours TIS after the effective date of the AD. Thereafter, repeat the visual inspection at intervals not to exceed 200 hours TIS until the airplane has accumulated 4,000 hours E:\FR\FM\22SEP1.SGM 22SEP1 59460 Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Proposed Rules TIS or until all 48 elevator torque tube attach fasteners are replaced, whichever occurs first. (iii) For airplanes that have accumulated 4,000 or more hours TIS as of the effective date of this AD, complete a one-time visual inspection within 200 hours TIS after the effective date of the AD. No repetitive inspections are required after completion of the one-time visual inspection. (2) If there are any loose, fretting, or incorrectly installed fasteners, remove the elevator and replace all 48 elevator torque tube attach fasteners (24 per side, with 12 each on the inboard and outboard elevator torque tube attach point) before further flight. Maintain proper alignment by marking each part prior to removal and by replacing one fastener at a time. Replacing all 48 fasteners is terminating action for the repetitive inspections required by paragraphs (g)(1)(i) and (ii) of this AD. (3) If all 48 fasteners were replaced before the effective date of this AD by following the instructions in paragraph (g)(2) of this AD, then the initial and recurring inspections detailed in paragraph (g)(1) of this AD are not required provided you report the information required by paragraph (h) of this AD. (h) Reporting Requirement Within 30 days after doing the initial inspection (regardless if loose, fretting, or incorrectly installed fasteners were found) or within 30 days after the effective date of this AD, whichever occurs later, and then within 30 days after each inspection where loose, fretting, or incorrectly installed fasteners were found, report the following information to the FAA at Wichita-COS@faa.gov: (1) Name and address of owner. (2) Date of the inspection. (3) Name, address, telephone number, and email address of person submitting the report. (4) Airplane serial number, registration number, and total hours TIS on the airplane at the time of the inspection. (5) If an earlier inspection identified loose, fretting, or incorrectly installed fasteners, identify the hours TIS on the airplane and which fasteners were replaced, if known, or if all fasteners were replaced. (6) If loose, fretting, or incorrectly installed fasteners were found, detailed information including a sketch or picture showing the location of the loose, fretting, or incorrectly installed fasteners and identification of any installed supplemental type certificates (STCs), alterations, repairs, or field approvals affecting the area of concern. (i) 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 currently 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 1 hour per response, including the time for reviewing VerDate Sep<11>2014 17:17 Sep 21, 2020 Jkt 250001 instructions, searching existing data sources, gathering and maintaining the data needed, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177–1524. (j) 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 the Related Information section 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. Notice of proposed rulemaking (NPRM). ACTION: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus SAS Model A350–941 and –1041 airplanes. This proposed AD was prompted by reports of migration of the bushings of the horizontal tail plane (HTP) lateral load fittings (LLFs) on the left- and right-hand sides during flight test. This proposed AD would require repetitive inspections for migration of the bushings of the HTP LLFs on the left- and right-hand sides, and terminating repair or modification of any affected bushing, as specified in a European Union Aviation Safety Agency (EASA), which will be incorporated by reference. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by November 6, 2020. SUMMARY: [Docket No. FAA–2020–0846; Project Identifier MCAI–2020–00806–T] 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 the material incorporated by reference (IBR) in this AD, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0846. RIN 2120–AA64 Examining the AD Docket (k) Related Information (1) For more information about this AD, contact Bobbie Kroetch, Aerospace Engineer, Wichita ACO Branch, FAA, 1801 Airport Rd, Wichita, KS 67209; phone: 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., One Cessna Boulevard, Wichita, KS 67215, telephone: 316–517–5800, email: teamturbopropsupport@txtav.com, internet: https://support.cessna.com. You may review this referenced service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued on September 15, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–20681 Filed 9–21–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 ADDRESSES: You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0846; or in person at Docket Operations E:\FR\FM\22SEP1.SGM 22SEP1

Agencies

[Federal Register Volume 85, Number 184 (Tuesday, September 22, 2020)]
[Proposed Rules]
[Pages 59457-59460]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-20681]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0811; Product Identifier 2019-CE-055-AD]
RIN 2120-AA64


Airworthiness Directives; Textron Aviation Inc. (Textron) 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Textron (type certificate previously held by Cessna 
Aircraft Company) Models 208 and 208B airplanes. This proposed AD was 
prompted by reports of loose elevator torque tube attach fasteners. 
This proposed AD would require repetitively inspecting the inboard and 
outboard elevator torque tube attachments for loose or incorrectly 
installed fasteners, replacing all fasteners if loose or incorrectly 
installed fasteners are found, and reporting the inspection results to 
the FAA. This AD also includes optional actions to terminate the 
repetitive inspections. The FAA is proposing this AD to address the 
unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by November 6, 
2020.

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., One Cessna Boulevard, Wichita, KS 67215: 
Telephone: 316-517-5800: email: [email protected]; 
internet: https://support.cessna.com. You may view this service 
information at the FAA, Airworthiness Products Section, Operational 
Safety Branch, 901 Locust St., Kansas City, MO 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-2020-
0811; 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 is listed above. 
Comments will be available in the AD docket shortly after receipt.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites 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-2020-0811; 
Product Identifier 2019-CE-055-AD'' at the beginning of your comments. 
The FAA will consider all comments received by

[[Page 59458]]

the closing date and may amend this NPRM because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The FAA will also post a report summarizing each substantive 
verbal contact it receives about this proposed AD.

Confidential Business Information

    Confidential Business Information (CBI) is commercial or financial 
information that is both customarily and actually treated as private by 
its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), 
CBI is exempt from public disclosure. If your comments responsive to 
this NPRM contain commercial or financial information that is 
customarily treated as private, that you actually treat as private, and 
that is relevant or responsive to this NPRM, it is important that you 
clearly designate the submitted comments as CBI. Please mark each page 
of your submission containing CBI as ``PROPIN.'' The FAA will treat 
such marked submissions as confidential under the FOIA, and they will 
not be placed in the public docket of this NPRM. Submissions containing 
CBI should be sent to Bobbie Kroetch, Aerospace Engineer, Wichita ACO 
Branch, FAA, 1801 Airport Road, Wichita, Kansas 67209. Any commentary 
that the FAA receives which is not specifically designated as CBI will 
be placed in the public docket for this rulemaking.

Discussion

    The FAA received reports of loose elevator torque tube attach 
fasteners on low flight time Textron Model 208B airplanes. Textron 
identified a quality escape affecting certain serial-numbered Model 208 
and 208B airplanes. Fastener holes in the inboard and outboard elevator 
torque tube connections may have been oversized and fasteners at the 
inboard and outboard torque tube connections may have been installed 
incorrectly.
    This condition, if not addressed, could result in failure of the 
elevator torque tube fasteners, leading to loss of elevator control and 
loss of controlled flight.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Task 27-30-00-290, Left and Right Elevator Torque 
Tube Attach Points (Borescope) Special Detailed Inspection, dated 
October 1, 2018, of the Cessna Model 208 Maintenance Manual (Task 27-
30-00-290). This service information contains procedures for performing 
a detailed borescope inspection of the left and right elevator torque 
tube attach points. 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

    The FAA also reviewed Textron Aviation Mandatory Caravan Service 
Bulletin CAB-27-06, dated October 14, 2019 (CAB-27-06). This service 
information contains instructions for visually inspecting the left and 
right elevator torque tube attach points for the presence of loose 
rivets and replacing loose or incorrectly installed rivets.

FAA's Determination

    The FAA is proposing this AD because it evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of this same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.'' This proposed AD also requires reporting the inspection 
results to the FAA.

Differences Between This Proposed AD and the Service Information

    Task 27-30-00-290 only specifies replacing loose fasteners. The 
proposed AD would require replacement of all 48 fasteners if any single 
inboard or outboard elevator torque tube attach fastener is found loose 
or incorrectly installed. The FAA determined based on field evidence 
that identification of one loose fastener often indicates other 
fasteners may be affected.
    CAB-27-06, which would not be incorporated by reference in this 
proposed AD, specifies performing an initial inspection within 800 
flight hours or 12 months from date of receipt, whichever occurs first. 
This proposed AD would require an initial inspection before the 
airplane accumulates 800 hours time-in-service (TIS) or within 200 
hours TIS after the AD effectivity date, whichever occurs later.
    CAB-27-06 also specifies, without sufficient data, that an 
inspection is not required for airplanes that have reached 4,000 hours. 
The FAA determined an inspection of high-time airplanes is necessary to 
verify whether these airplanes are affected. This proposed AD would 
require a one-time visual inspection for airplanes that have already 
accumulated 4,000 hours TIS.

Costs of Compliance

    The FAA estimates that this proposed AD affects 232 airplanes of 
U.S. registry.
    The FAA estimates the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection......................  1 work-hour x $85   Not applicable....  $85 per inspection  $19,720 per
                                   per hour = $85.                         cycle.              inspection cycle.
Reporting Requirement...........  1 work-hour x $85   Not applicable....  $85 per report....  $19,720 per
                                   per hour = $85.                                             report.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacements that would be required based on the results of the 
proposed inspection. The FAA has no way of determining the number of 
airplanes that might need these replacements:

[[Page 59459]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Fastener Replacement: All 48 Fasteners........  16 work-hours x $85 per hour =               $10         $1,370.
                                                 $1,360.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. The FAA does not control warranty coverage for 
affected individuals. As a result, the FAA has included all costs in 
this cost estimate.

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 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 currently 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 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, completing and reviewing the collection of 
information. All responses to this collection of information are 
mandatory. Send comments regarding this burden estimate or any other 
aspect of this collection of information, including suggestions for 
reducing this burden to: Information Collection Clearance Officer, 
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 
76177-1524.

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.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements 
under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    The FAA 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) Will not affect intrastate aviation in Alaska, and
    (3) 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. (Type Certificate Previously Held by Cessna 
Aircraft Company): Docket No. FAA-2020-0811; Product Identifier 
2019-CE-055-AD.

(a) Comments Due Date

    The FAA must receive comments by November 6, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Textron Aviation Inc. (Textron) (type 
certificate previously held by Cessna Aircraft Company) Model 208 
airplanes, serial numbers 20800564 through 20800594 and 20800603 
through 20800605; and Model 208B airplanes, serial numbers 208B5141 
through 208B5285, 208B5287 through 208B5305, 208B5307 through 
208B5312, 208B5314, 208B5316 through 208B5344, 208B5346 through 
208B5350, 208B5353, 208B5354, 208B5356 through 208B5359, 208B5362 
through 208B5366, 208B5401, 208B5403, 208B5404, and 208B5408; 
certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code: 5520, Elevator Structure.

(e) Unsafe Condition

    This AD was prompted by reports loose elevator torque tube 
attach fasteners. The FAA is issuing this AD to detect and correct 
loosening and eventual failure of the elevator torque tube attach 
fasteners. The unsafe condition, if not addressed, could result in 
loss of elevator control, resulting in loss of control of the 
airplane.

(f) Compliance

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

(g) Inspection and Fastener Replacement

    (1) At the following compliance times, inspect each inboard and 
outboard elevator torque tube attach fastener for looseness and 
fretting by following sections 2.C. and 2.D. of Task 27-30-00-290, 
Left and Right Elevator Torque Tube Attach Points (Borescope) 
Special Detailed Inspection, dated October 1, 2018, of the Cessna 
Model 208 Maintenance Manual. You must also inspect for incorrectly 
installed fasteners.
    (i) For airplanes that have accumulated less than 800 hours 
time-in-service (TIS) as of the effective date of this AD, complete 
the initial inspection before the airplane accumulates 800 hours TIS 
or within 200 hours TIS after the effective date of the AD, 
whichever occurs later. Thereafter, repeat the visual inspection at 
intervals not to exceed 200 hours TIS until the airplane has 
accumulated 4,000 hours TIS or until all 48 elevator torque tube 
attach fasteners are replaced, whichever occurs first.
    (ii) For airplanes that have accumulated 800 or more hours TIS 
but less than 4,000 hours TIS as of the effective date of this AD, 
complete the initial inspection within 200 hours TIS after the 
effective date of the AD. Thereafter, repeat the visual inspection 
at intervals not to exceed 200 hours TIS until the airplane has 
accumulated 4,000 hours

[[Page 59460]]

TIS or until all 48 elevator torque tube attach fasteners are 
replaced, whichever occurs first.
    (iii) For airplanes that have accumulated 4,000 or more hours 
TIS as of the effective date of this AD, complete a one-time visual 
inspection within 200 hours TIS after the effective date of the AD. 
No repetitive inspections are required after completion of the one-
time visual inspection.
    (2) If there are any loose, fretting, or incorrectly installed 
fasteners, remove the elevator and replace all 48 elevator torque 
tube attach fasteners (24 per side, with 12 each on the inboard and 
outboard elevator torque tube attach point) before further flight. 
Maintain proper alignment by marking each part prior to removal and 
by replacing one fastener at a time. Replacing all 48 fasteners is 
terminating action for the repetitive inspections required by 
paragraphs (g)(1)(i) and (ii) of this AD.
    (3) If all 48 fasteners were replaced before the effective date 
of this AD by following the instructions in paragraph (g)(2) of this 
AD, then the initial and recurring inspections detailed in paragraph 
(g)(1) of this AD are not required provided you report the 
information required by paragraph (h) of this AD.

(h) Reporting Requirement

    Within 30 days after doing the initial inspection (regardless if 
loose, fretting, or incorrectly installed fasteners were found) or 
within 30 days after the effective date of this AD, whichever occurs 
later, and then within 30 days after each inspection where loose, 
fretting, or incorrectly installed fasteners were found, report the 
following information to the FAA at [email protected]:
    (1) Name and address of owner.
    (2) Date of the inspection.
    (3) Name, address, telephone number, and email address of person 
submitting the report.
    (4) Airplane serial number, registration number, and total hours 
TIS on the airplane at the time of the inspection.
    (5) If an earlier inspection identified loose, fretting, or 
incorrectly installed fasteners, identify the hours TIS on the 
airplane and which fasteners were replaced, if known, or if all 
fasteners were replaced.
    (6) If loose, fretting, or incorrectly installed fasteners were 
found, detailed information including a sketch or picture showing 
the location of the loose, fretting, or incorrectly installed 
fasteners and identification of any installed supplemental type 
certificates (STCs), alterations, repairs, or field approvals 
affecting the area of concern.

(i) 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 currently 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 1 hour per response, including the 
time for reviewing instructions, searching existing data sources, 
gathering and maintaining the data needed, completing and reviewing 
the collection of information. All responses to this collection of 
information are mandatory. Send comments regarding this burden 
estimate or any other aspect of this collection of information, 
including suggestions for reducing this burden to: Information 
Collection Clearance Officer, Federal Aviation Administration, 10101 
Hillwood Parkway, Fort Worth, TX 76177-1524.

(j) 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 the Related Information section 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.

(k) Related Information

    (1) For more information about this AD, contact Bobbie Kroetch, 
Aerospace Engineer, Wichita ACO Branch, FAA, 1801 Airport Rd, 
Wichita, KS 67209; phone: 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., One Cessna Boulevard, Wichita, KS 67215, 
telephone: 316-517-5800, email: [email protected], 
internet: https://support.cessna.com. You may review this referenced 
service information at the FAA, Airworthiness Products Section, 
Operational Safety Branch, 901 Locust, Kansas City, Missouri 64106. 
For information on the availability of this material at the FAA, 
call (816) 329-4148.

    Issued on September 15, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-20681 Filed 9-21-20; 8:45 am]
BILLING CODE 4910-13-P