Airworthiness Directives; Textron Aviation, Inc. Airplanes, 58813-58816 [2016-20073]

Download as PDF Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations 2016, for related information. The MCAI can be found in the AD docket on the Internet at: https://www.regulations.gov/document?D= FAA–2016–7026–0002. (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) PILATUS Aircraft Ltd. PC–7 Service Bulletin No: 53–013; dated February 25, 2016; and (ii) PILATUS Aircraft Ltd. PC–7 Service Bulletin No: 53–014, dated February 25, 2016. (3) For PILATUS Aircraft Ltd. service information identified in this AD, contact PILATUS Aircraft Ltd., Customer Technical Support (MCC), P.O. Box 992, CH–6371 Stans, Switzerland; phone: +41 (0)41 619 67 74; fax: +41 (0)41 619 67 73; email: techsupport@pilatus-aircraft.com; Internet: http://www.pilatus-aircraft.com. (4) You may view this service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Kansas City, Missouri, on August 17, 2016. Pat Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–20074 Filed 8–25–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8992; Directorate Identifier 2016–CE–021–AD; Amendment 39–18621; AD 2016–17–08] RIN 2120–AA64 Airworthiness Directives; Textron Aviation, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ehiers on DSK5VPTVN1PROD with RULES AGENCY: We are superseding Airworthiness Directive (AD) 2016–07– 24 for all Textron Aviation, Inc. Models 310 through 310R, E310H, E310J, T310P SUMMARY: VerDate Sep<11>2014 14:39 Aug 25, 2016 Jkt 238001 through T310R, 310J–1, 320 through 320F, 320–1, 335, 340, 340A, 401 through 401B, 402 through 402C, 411, 411A, 414, 414A, and 421 through 421C airplanes (type certificates 3A10, 3A25, and A7CE previously held by Cessna Aircraft Company). AD 2016–07–24 required replacement and repetitive inspections of the hardware securing the elevator trim tab push-pull rod. This AD retains the actions for AD 2016–07–24 but revises the repetitive inspection intervals and allows for a longer bolt for the attachment of the elevator trim tab actuator rod end to the push-pull tube connection and/or for the elevator trim tab horn end to the push-pull tube connection. This AD was prompted by comments indicating difficulties with bolt installation and requesting a revision to repetitive inspection intervals to coincide with established inspection intervals. We are issuing this AD to prevent jamming of the elevator trim tab in a position outside the normal limits of travel due to the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod, which could result in loss of control. DATES: This AD is effective September 12, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 12, 2016. We must receive any comments on this AD by October 11, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact Textron Aviation Customer Service, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517–5800; fax: (316) 517–7271; email: customercare@txtav.com; Internet: https://support.cessna.com/custsupt/ csupport/newlogin.jsp. You may review this referenced service information at the FAA, Small Airplane Directorate, PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 58813 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 8992. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 8992; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Adam Hein, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 S. Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946–4116; fax: (316) 946–4107; email: adam.hein@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On March 30, 2016, we issued AD 2016–07–24, Amendment 39–18469 (81 FR 21250, April 11, 2016), (‘‘AD 2016– 07–24’’), for all Textron Aviation, Inc. Models 310 through 310R, E310H, E310J, T310P through T310R, 310J–1, 320 through 320F, 320–1, 335, 340, 340A, 401 through 401B, 402 through 402C, 411, 411A, 414, 414A, and 421 through 421C airplanes (type certificates 3A10, 3A25, and A7CE previously held by Cessna Aircraft Company). AD 2016– 07–24 required replacing the hardware connecting the elevator trim tab pushpull rod to the elevator trim tab actuator and elevator trim tab. AD 2016–07–24 resulted from accident reports on Textron Aviation, Inc. Models T310Q, 310Q, and 402B airplanes; lessons learned in accident investigation support; and analysis of past accidents. The analysis of National Transportation Safety Board (NTSB) determination of probable cause indicated that following the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod, the elevator trim tab may jam in a position outside the normal limits of travel. We issued AD 2016–07–24 to require replacement and repetitive inspections of the hardware securing the elevator trim tab push-pull rod. E:\FR\FM\26AUR1.SGM 26AUR1 58814 Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations Actions Since AD 2016–07–24 Was Issued Since we issued AD 2016–07–24, we have received reports of difficulties in installing the required bolt, part number (P/N) NAS464P3–8, because it was found in some cases to be too short to properly fasten with a cotter pin as required by the AD. It was also determined beneficial to revise the repetitive inspection intervals to better coincide with the standard established inspection intervals for these airplanes. We are issuing this AD to correct the unsafe condition on these products. Related Service Information Under 1 CFR Part 51 We reviewed Textron Aviation, Inc. (Cessna Aircraft Company) Multi-engine Service Bulletin No. MEB–27–02, Revision 1, dated June 15, 2016. The service information describes procedures for replacing the hardware connecting the elevator trim tab pushpull rod to the elevator trim tab actuator and elevator trim tab. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or are impracticable and that good cause exists for making this amendment effective in less than 30 days. develop in other products of the same type design. AD Requirements Comments Invited This AD requires replacement and repetitive inspection of the elevator trim tab push-pull rod connecting hardware. This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA–2016–8992 and directorate identifier 2016–CE–021–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Differences Between the AD and the Service Information Due to the immediate safety of flight condition of this AD action, we are requiring replacement of the hardware within 90 days after the effective date of this AD rather than the potential of up to a year as allowed in the service information. The kit referenced in the service bulletin contains only standard parts that may be procured from other sources. FAA’s Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod may result in jamming of the elevator trim tab beyond normal limits, which could result in loss of ability to control the airplane. Therefore, we find that notice and opportunity for prior public comment Costs of Compliance We estimate that this AD affects 5,066 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Elevator trim tab push-pull 5 work-hour × $85 per hour = $425 .................................. rod hardware replacement. Repetitive Inspection ........... 1 work-hour × $85 per hour = $85 .................................... We estimate the following costs to do any necessary replacements that would be required based on the results of the Cost per product Parts cost Cost on U.S. operators $42 ........................ $467 $2,365,822 Not applicable ....... 85 430,610 inspection. This is the same replacement that is initially required by this AD. We have no way of determining the number of aircraft that might need this repetitive on-condition replacement: ON-CONDITION COSTS Action Labor cost Elevator trim tab push-pull rod hardware replacement. 5 work-hours × $85 per hour = $425 ........................................................ ehiers on DSK5VPTVN1PROD with RULES Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more VerDate Sep<11>2014 14:39 Aug 25, 2016 Jkt 238001 Parts cost 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 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 $42 Cost per product $467 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 E:\FR\FM\26AUR1.SGM 26AUR1 Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (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 removing Airworthiness Directive (AD) 2016–07–24, Amendment 39–18469 (81 FR 21250, April 11, 2016) and adding the following new AD: ■ 2016–17–08 Textron Aviation, Inc.: Amendment 39–18621; Docket No. FAA–2016–8992; Directorate Identifier 2016–CE–021–AD. ehiers on DSK5VPTVN1PROD with RULES (a) Effective Date This AD is effective September 12, 2016. (b) Affected ADs This AD replaces AD 2016–07–24, Amendment 39–18469 (81 FR 21250, April 11, 2016) (‘‘AD 2016–07–24’’). (c) Applicability This AD applies to Textron Aviation, Inc. Models 310 through 310R, E310H, E310J, T310P through T310R, 310J–1, 320 through VerDate Sep<11>2014 14:39 Aug 25, 2016 Jkt 238001 320F, 320–1, 335, 340, 340A, 401 through 401B, 402 through 402C, 411, 411A, 414, 414A, and 421 through 421C airplanes (type certificates 3A10, 3A25, and A7CE previously held by Cessna Aircraft Company), all serial numbers, certificated in any category. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 2731, Elevator Tab Control System. (e) Unsafe Condition This AD supersedes AD 2016–07–24, which required replacement and repetitive inspections of the hardware securing the elevator trim tab push-pull rod. This AD retains the actions for AD 2016–07–24 but revises the repetitive inspection intervals and allows for a longer bolt for the attachment of the elevator trim tab actuator rod end to the push-pull tube connection and/or for the elevator trim tab horn end to the push-pull tube connection. This AD was prompted by comments indicating difficulties with bolt installation and requesting a revision to repetitive inspection intervals to coincide with established inspection intervals. We are issuing this AD to prevent jamming of the elevator trim tab in a position outside the normal limits of travel due to the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod, which could result in loss of control. (f) Actions and Compliance Do the actions in paragraphs (f)(1) through (3) of this AD. If paragraph (f)(1) of this AD has already been done before September 12, 2016 (the effective date of this AD) following either Textron Aviation, Inc. (Cessna) Multiengine Service Bulletin (SB) No. MEB–27–02, dated February 29, 2016 (see paragraph (g) of this AD) or Textron Aviation, Inc. (Cessna) Multi-engine Service Bulletin (SB) No. MEB– 27–02, Revision 1, dated June 15, 2016, then credit can be taken and the only required actions are the repetitive actions of paragraphs (f)(2) and (3) of this AD. (1) Within the next 90 days after September 12, 2016 (the effective date of this AD), replace the elevator trim tab push-pull rod attachment hardware on the elevator trim tab actuator and the trim tab ends of the pushpull rod following steps 3 through 6 of the accomplishment instructions in Textron Aviation, Inc. (Cessna) Multi-engine Service Bulletin (SB) No. MEB–27–02, Revision 1, dated June 15, 2016. (2) Following the replacement required in paragraph (f)(1) of this AD or the replacement or previous repetitive general visual inspection done per AD 2016–07–24, whichever occurs later, repetitively conduct general visual inspections of the elevator trim tab push-pull rod attachment hardware on the elevator trim tab actuator and the trim tab ends of the push-pull rod at intervals not to exceed 110 hours TIS or 12 months, whichever occurs first. Before further flight, replace the hardware if necessary following the Compliance NOTE on page 1 of Textron Aviation, Inc. (Cessna) Multi-engine Service Bulletin (SB) No. MEB–27–02, Revision 1, dated June 15, 2016. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 58815 Note 1 to paragraph (f)(2) of this AD: The intent is to require these repetitive inspections during your regular maintenance schedule. (3) After September 12, 2016 (the effective date of this AD), any time the elevator trim tab push-pull rod attachment hardware on the elevator trim tab actuator and/or trim tab ends of the push-pull rod is removed for any reason, discard the old hardware (bolt, nut, washer and cotter pin) and replace with new hardware following steps 4 and/or step 6 of Textron Aviation, Inc. (Cessna) Multi-engine Service Bulletin (SB) No. MEB–27–02, Revision 1, dated June 15, 2016. (g) Credit for Actions Accomplished in Accordance With Previous Service Information This AD allows credit for the actions required in paragraphs (f)(1) of this AD if done before September 12, 2016 (the effective date of this AD) following the instructions of Textron Aviation, Inc. (Cessna) Multi-engine Service Bulletin (SB) No. MEB–27–02, dated February 29, 2016. (h) Special Flight Permit Special flight permits are allowed for this AD per 14 CFR 39.23 with the following limitation: Before flight a pre-flight visual inspection is required of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod. Confirmation of the presence of a castellated nut and cotter pin is required. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Wichita ACO, 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 ACO, send it to the attention of the person identified in paragraph (i) 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. (3) AMOCs approved previously for AD 2016–07–24 are valid as AMOCs for this AD. (j) Related Information For more information about this AD, contact Adam Hein, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 S. Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946–4116; fax: (316) 946–4107; email: adam.hein@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on September 12, 2016 (the effective date of this AD). E:\FR\FM\26AUR1.SGM 26AUR1 58816 Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations (i). Textron Aviation, Inc. (Cessna) Multiengine Service Bulletin (SB) No. MEB–27–02, Revision 1, dated June 15, 2016. (ii) Reserved. (4) For Textron Aviation, Inc. (Cessna) service information identified in this AD, contact Textron Aviation Customer Service, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517–5800; fax: (316) 517– 7271; email: customercare@ cessna.textron.com; Internet: https:// support.cessna.com/custsupt/csupport/ newlogin.jsp. (5) You may view this service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016–8992. (6) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Kansas City, Missouri, on August 17, 2016. Pat Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–20073 Filed 8–25–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–4221; Directorate Identifier 2015–NM–167–AD; Amendment 39–18619; AD 2016–17–06] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767–200 and –300 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft pressure bulkhead web to pressure chord joint is subject to widespread fatigue damage (WFD). This AD requires repetitive high frequency eddy current (HFEC) inspections of the aft pressure bulkhead web at fasteners common to the bulkhead web and pressure chord, around the entire circumference of the pressure chord, for any crack, and repair of cracks. We are ehiers on DSK5VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 14:39 Aug 25, 2016 Jkt 238001 issuing this AD to detect and correct cracks in the aft pressure bulkhead web. Such cracking could result in the loss of structural integrity of the airplane. DATES: This AD is effective September 30, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 30, 2016. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 4221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 4221; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6447; fax: 425–917–6590; email: wayne.lockett@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 767–200 and –300 series airplanes. The NPRM published in the Federal Register on March 8, 2016 (81 FR 12047) (‘‘the NPRM’’). The NPRM was prompted by an evaluation by the DAH PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 indicating that the aft pressure bulkhead web to pressure chord joint is subject to WFD. The NPRM proposed to require repetitive HFEC inspections of the aft pressure bulkhead web at fasteners common to the bulkhead web and pressure chord, around the entire circumference of the pressure chord, for any crack, and repair of cracks. We are issuing this AD to detect and correct cracks in the aft pressure bulkhead web. Such cracking could result in the loss of structural integrity of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response. Boeing and United Airlines supported the NPRM. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing supplemental type certificate (STC) ST01920SE does not affect the actions specified in the proposed AD. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as paragraph (c)(1), and added new paragraph (c)(2) to this AD to state that installation of STC ST01920SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 767–53A0268, dated April 1, 2015. The service information describes procedures for HFEC inspections of the aft pressure bulkhead web at fasteners E:\FR\FM\26AUR1.SGM 26AUR1

Agencies

[Federal Register Volume 81, Number 166 (Friday, August 26, 2016)]
[Rules and Regulations]
[Pages 58813-58816]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-20073]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8992; Directorate Identifier 2016-CE-021-AD; 
Amendment 39-18621; AD 2016-17-08]
RIN 2120-AA64


Airworthiness Directives; Textron Aviation, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2016-07-24 for 
all Textron Aviation, Inc. Models 310 through 310R, E310H, E310J, T310P 
through T310R, 310J-1, 320 through 320F, 320-1, 335, 340, 340A, 401 
through 401B, 402 through 402C, 411, 411A, 414, 414A, and 421 through 
421C airplanes (type certificates 3A10, 3A25, and A7CE previously held 
by Cessna Aircraft Company). AD 2016-07-24 required replacement and 
repetitive inspections of the hardware securing the elevator trim tab 
push-pull rod. This AD retains the actions for AD 2016-07-24 but 
revises the repetitive inspection intervals and allows for a longer 
bolt for the attachment of the elevator trim tab actuator rod end to 
the push-pull tube connection and/or for the elevator trim tab horn end 
to the push-pull tube connection. This AD was prompted by comments 
indicating difficulties with bolt installation and requesting a 
revision to repetitive inspection intervals to coincide with 
established inspection intervals. We are issuing this AD to prevent 
jamming of the elevator trim tab in a position outside the normal 
limits of travel due to the loss of the attachment hardware connecting 
the elevator trim tab actuator to the elevator trim tab push-pull rod, 
which could result in loss of control.

DATES: This AD is effective September 12, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
12, 2016.
    We must receive any comments on this AD by October 11, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this final rule, contact 
Textron Aviation Customer Service, P.O. Box 7706, Wichita, Kansas 
67277; telephone: (316) 517-5800; fax: (316) 517-7271; email: 
customercare@txtav.com; Internet: https://support.cessna.com/custsupt/csupport/newlogin.jsp. You may review this referenced service 
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas 
City, Missouri 64106. For information on the availability of this 
material at the FAA, call (816) 329-4148. It is also available on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-8992.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8992; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Adam Hein, Aerospace Engineer, Wichita 
Aircraft Certification Office, FAA, 1801 S. Airport Road, Room 100, 
Wichita, Kansas 67209; phone: (316) 946-4116; fax: (316) 946-4107; 
email: adam.hein@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    On March 30, 2016, we issued AD 2016-07-24, Amendment 39-18469 (81 
FR 21250, April 11, 2016), (``AD 2016-07-24''), for all Textron 
Aviation, Inc. Models 310 through 310R, E310H, E310J, T310P through 
T310R, 310J-1, 320 through 320F, 320-1, 335, 340, 340A, 401 through 
401B, 402 through 402C, 411, 411A, 414, 414A, and 421 through 421C 
airplanes (type certificates 3A10, 3A25, and A7CE previously held by 
Cessna Aircraft Company). AD 2016-07-24 required replacing the hardware 
connecting the elevator trim tab push-pull rod to the elevator trim tab 
actuator and elevator trim tab. AD 2016-07-24 resulted from accident 
reports on Textron Aviation, Inc. Models T310Q, 310Q, and 402B 
airplanes; lessons learned in accident investigation support; and 
analysis of past accidents. The analysis of National Transportation 
Safety Board (NTSB) determination of probable cause indicated that 
following the loss of the attachment hardware connecting the elevator 
trim tab actuator to the elevator trim tab push-pull rod, the elevator 
trim tab may jam in a position outside the normal limits of travel. We 
issued AD 2016-07-24 to require replacement and repetitive inspections 
of the hardware securing the elevator trim tab push-pull rod.

[[Page 58814]]

Actions Since AD 2016-07-24 Was Issued

    Since we issued AD 2016-07-24, we have received reports of 
difficulties in installing the required bolt, part number (P/N) 
NAS464P3-8, because it was found in some cases to be too short to 
properly fasten with a cotter pin as required by the AD. It was also 
determined beneficial to revise the repetitive inspection intervals to 
better coincide with the standard established inspection intervals for 
these airplanes. We are issuing this AD to correct the unsafe condition 
on these products.

Related Service Information Under 1 CFR Part 51

    We reviewed Textron Aviation, Inc. (Cessna Aircraft Company) Multi-
engine Service Bulletin No. MEB-27-02, Revision 1, dated June 15, 2016. 
The service information describes procedures for replacing the hardware 
connecting the elevator trim tab push-pull rod to the elevator trim tab 
actuator and elevator trim tab. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section.

FAA's Determination

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

AD Requirements

    This AD requires replacement and repetitive inspection of the 
elevator trim tab push-pull rod connecting hardware.

Differences Between the AD and the Service Information

    Due to the immediate safety of flight condition of this AD action, 
we are requiring replacement of the hardware within 90 days after the 
effective date of this AD rather than the potential of up to a year as 
allowed in the service information.
    The kit referenced in the service bulletin contains only standard 
parts that may be procured from other sources.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because the 
loss of the attachment hardware connecting the elevator trim tab 
actuator to the elevator trim tab push-pull rod may result in jamming 
of the elevator trim tab beyond normal limits, which could result in 
loss of ability to control the airplane. Therefore, we find that notice 
and opportunity for prior public comment are impracticable and that 
good cause exists for making this amendment effective in less than 30 
days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
the docket number FAA-2016-8992 and directorate identifier 2016-CE-021-
AD at the beginning of your comments. We specifically invite comments 
on the overall regulatory, economic, environmental, and energy aspects 
of this AD. We will consider all comments received by the closing date 
and may amend this AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 5,066 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
            Action                    Labor cost               Parts cost             product        operators
----------------------------------------------------------------------------------------------------------------
Elevator trim tab push-pull     5 work-hour x $85 per   $42.....................            $467      $2,365,822
 rod hardware replacement.       hour = $425.
Repetitive Inspection.........  1 work-hour x $85 per   Not applicable..........              85         430,610
                                 hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. This is 
the same replacement that is initially required by this AD. We have no 
way of determining the number of aircraft that might need this 
repetitive on-condition replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Elevator trim tab push-pull rod hardware     5 work-hours x $85 per hour = $425.             $42            $467
 replacement.
----------------------------------------------------------------------------------------------------------------

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

[[Page 58815]]

that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends part 39 of the Federal Aviation 
Regulations (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 removing Airworthiness Directive (AD) 
2016-07-24, Amendment 39-18469 (81 FR 21250, April 11, 2016) and adding 
the following new AD:

2016-17-08 Textron Aviation, Inc.: Amendment 39-18621; Docket No. 
FAA-2016-8992; Directorate Identifier 2016-CE-021-AD.

(a) Effective Date

    This AD is effective September 12, 2016.

(b) Affected ADs

    This AD replaces AD 2016-07-24, Amendment 39-18469 (81 FR 21250, 
April 11, 2016) (``AD 2016-07-24'').

(c) Applicability

    This AD applies to Textron Aviation, Inc. Models 310 through 
310R, E310H, E310J, T310P through T310R, 310J-1, 320 through 320F, 
320-1, 335, 340, 340A, 401 through 401B, 402 through 402C, 411, 
411A, 414, 414A, and 421 through 421C airplanes (type certificates 
3A10, 3A25, and A7CE previously held by Cessna Aircraft Company), 
all serial numbers, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 2731, Elevator Tab Control System.

(e) Unsafe Condition

    This AD supersedes AD 2016-07-24, which required replacement and 
repetitive inspections of the hardware securing the elevator trim 
tab push-pull rod. This AD retains the actions for AD 2016-07-24 but 
revises the repetitive inspection intervals and allows for a longer 
bolt for the attachment of the elevator trim tab actuator rod end to 
the push-pull tube connection and/or for the elevator trim tab horn 
end to the push-pull tube connection. This AD was prompted by 
comments indicating difficulties with bolt installation and 
requesting a revision to repetitive inspection intervals to coincide 
with established inspection intervals. We are issuing this AD to 
prevent jamming of the elevator trim tab in a position outside the 
normal limits of travel due to the loss of the attachment hardware 
connecting the elevator trim tab actuator to the elevator trim tab 
push-pull rod, which could result in loss of control.

(f) Actions and Compliance

    Do the actions in paragraphs (f)(1) through (3) of this AD. If 
paragraph (f)(1) of this AD has already been done before September 
12, 2016 (the effective date of this AD) following either Textron 
Aviation, Inc. (Cessna) Multi-engine Service Bulletin (SB) No. MEB-
27-02, dated February 29, 2016 (see paragraph (g) of this AD) or 
Textron Aviation, Inc. (Cessna) Multi-engine Service Bulletin (SB) 
No. MEB-27-02, Revision 1, dated June 15, 2016, then credit can be 
taken and the only required actions are the repetitive actions of 
paragraphs (f)(2) and (3) of this AD.
    (1) Within the next 90 days after September 12, 2016 (the 
effective date of this AD), replace the elevator trim tab push-pull 
rod attachment hardware on the elevator trim tab actuator and the 
trim tab ends of the push-pull rod following steps 3 through 6 of 
the accomplishment instructions in Textron Aviation, Inc. (Cessna) 
Multi-engine Service Bulletin (SB) No. MEB-27-02, Revision 1, dated 
June 15, 2016.
    (2) Following the replacement required in paragraph (f)(1) of 
this AD or the replacement or previous repetitive general visual 
inspection done per AD 2016-07-24, whichever occurs later, 
repetitively conduct general visual inspections of the elevator trim 
tab push-pull rod attachment hardware on the elevator trim tab 
actuator and the trim tab ends of the push-pull rod at intervals not 
to exceed 110 hours TIS or 12 months, whichever occurs first. Before 
further flight, replace the hardware if necessary following the 
Compliance NOTE on page 1 of Textron Aviation, Inc. (Cessna) Multi-
engine Service Bulletin (SB) No. MEB-27-02, Revision 1, dated June 
15, 2016.

    Note 1 to paragraph (f)(2) of this AD: The intent is to require 
these repetitive inspections during your regular maintenance 
schedule.

    (3) After September 12, 2016 (the effective date of this AD), 
any time the elevator trim tab push-pull rod attachment hardware on 
the elevator trim tab actuator and/or trim tab ends of the push-pull 
rod is removed for any reason, discard the old hardware (bolt, nut, 
washer and cotter pin) and replace with new hardware following steps 
4 and/or step 6 of Textron Aviation, Inc. (Cessna) Multi-engine 
Service Bulletin (SB) No. MEB-27-02, Revision 1, dated June 15, 
2016.

(g) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    This AD allows credit for the actions required in paragraphs 
(f)(1) of this AD if done before September 12, 2016 (the effective 
date of this AD) following the instructions of Textron Aviation, 
Inc. (Cessna) Multi-engine Service Bulletin (SB) No. MEB-27-02, 
dated February 29, 2016.

 (h) Special Flight Permit

    Special flight permits are allowed for this AD per 14 CFR 39.23 
with the following limitation: Before flight a pre-flight visual 
inspection is required of the attachment hardware connecting the 
elevator trim tab actuator to the elevator trim tab push-pull rod. 
Confirmation of the presence of a castellated nut and cotter pin is 
required.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Wichita ACO, 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 
ACO, send it to the attention of the person identified in paragraph 
(i) 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.
    (3) AMOCs approved previously for AD 2016-07-24 are valid as 
AMOCs for this AD.

 (j) Related Information

    For more information about this AD, contact Adam Hein, Aerospace 
Engineer, Wichita Aircraft Certification Office, FAA, 1801 S. 
Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946-
4116; fax: (316) 946-4107; email: adam.hein@faa.gov.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
September 12, 2016 (the effective date of this AD).

[[Page 58816]]

    (i). Textron Aviation, Inc. (Cessna) Multi-engine Service 
Bulletin (SB) No. MEB-27-02, Revision 1, dated June 15, 2016.
    (ii) Reserved.
    (4) For Textron Aviation, Inc. (Cessna) service information 
identified in this AD, contact Textron Aviation Customer Service, 
P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; 
fax: (316) 517-7271; email: customercare@cessna.textron.com; 
Internet: https://support.cessna.com/custsupt/csupport/newlogin.jsp.
    (5) You may view this service information at the FAA, Small 
Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2016-8992.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on August 17, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-20073 Filed 8-25-16; 8:45 am]
 BILLING CODE 4910-13-P