Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes, 66175-66178 [2018-27899]

Download as PDF Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Proposed Rules 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): ■ The Boeing Company: Docket No. FAA– 2018–1011; Product Identifier 2018– NM–131–AD. (a) Comments Due Date We must receive comments by February 11, 2019. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 767–200, –300, –300F, and –400ER series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/Furnishings. (e) Unsafe Condition This AD was prompted by reports of uncommanded movements of the Captain’s and First Officer’s seats. We are issuing this AD to address uncommanded movement of the Captain’s and First Officer’s seats. An uncommanded seat movement during a critical part of a flight, such as take-off or landing, could cause a flight control obstruction or unintended flight control input, which could result in the loss of the ability to control the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. amozie on DSK3GDR082PROD with PROPOSALS1 (g) Seat Identification and On-Condition Actions Within 36 months after the effective date of this AD, do an inspection to determine the part number, and serial number as applicable, of the Captain’s and First Officer’s seats, and do all applicable oncondition actions, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–25– 0539, Revision 1, dated July 17, 2018. (h) Detailed Inspection and Repetitive Checks of Horizontal Movement System and On-Condition Actions Except as specified in paragraph (i) of this AD: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 767–25– 0549, Revision 1, dated August 10, 2018 (‘‘BSASB 767–25–0549, Revision 1’’), do all applicable actions identified as ‘‘RC’’ VerDate Sep<11>2014 17:37 Dec 21, 2018 Jkt 247001 (required for compliance) in, and in accordance with, the Accomplishment Instructions of BSASB 767–25–0549, Revision 1. (i) Exceptions to Service Information Specifications For purposes of determining compliance with the requirements of this AD: Where BSASB 767–25–0549, Revision 1, uses the phrase ‘‘the original issue date of this service bulletin,’’ this AD requires using ‘‘the effective date of this AD.’’ (j) Optional Terminating Action for Repetitive Checks (1) For Group 1, Configuration 2 and 4 airplanes identified in BSASB 767–25–0549, Revision 1: Installation of a serviceable Captain’s seat, as specified in, and in accordance with, the Accomplishment Instructions of BSASB 767–25–0549, Revision 1, terminates the repetitive checks of the Captain’s seat as required by paragraph (h) of this AD for that airplane only. (2) For Group 1, Configuration 3 and 4 airplanes: Installation of a serviceable First Officer’s seat BSASB 767–25–0549, Revision 1, as specified in, and in accordance with, the Accomplishment Instructions of BSASB 767–25–0549, Revision 1, terminates the repetitive checks of the First Officer’s seat as required by paragraph (h) of this AD for that airplane only. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (l)(1) of this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov. (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) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 66175 substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information (1) For more information about this AD, contact Brandon Lucero, Aerospace Engineer, Cabin Safety and Environmental Systems Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3569; email: Brandon.Lucero@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on December 13, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–27882 Filed 12–21–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–1058; Product Identifier 2018–CE–051–AD] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Model PC–6, PC–6/350, PC–6/350–H1, PC–6/350–H2, PC–6/A, PC–6/A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/B2–H2, PC–6/B2– H4, PC–6/C–H2, PC–6/C1–H2, PC–6– H1, and PC–6–H2 airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify SUMMARY: E:\FR\FM\26DEP1.SGM 26DEP1 66176 Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Proposed Rules amozie on DSK3GDR082PROD with PROPOSALS1 and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as sheared or missing rivets on the horizontal stabilizer hinge bracket assemblies. We are issuing this proposed AD to require actions to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 11, 2019. ADDRESSES: You may send comments 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 proposed 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@pilatusaircraft.com; internet: http:// www.pilatus-aircraft.com. You may review this referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Examining the AD Docket You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 1058; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; fax: (816) 329–4090; email: doug.rudolph@faa.gov. SUPPLEMENTARY INFORMATION: VerDate Sep<11>2014 17:37 Dec 21, 2018 Jkt 247001 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2018–1058; Product Identifier 2018–CE–051–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No. 2018– 0217, dated October 10, 2018 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During a routine inspection, the rivets of the hinge bracket assemblies on a Pilatus PC– 6 were found to be sheared or missing. Investigation results identified that this was most likely due to application of too much force to the ends of the horizontal stabilizer during ground handling. This condition, if not detected and corrected, could lead to failure of the primary horizontal stabilizer load path and consequent separation of the horizontal stabilizer, possibly resulting in loss of control of the aeroplane. To address this potential unsafe condition, Pilatus Aircraft Ltd issued the SB [service bulletin] to provide applicable inspection instructions. For the reasons described above, this [EASA] AD requires a one-time inspection of the affected parts and the horizontal stabilizer front spar attachment area and, depending on findings, accomplishment of applicable corrective action(s). This [EASA] AD also requires, before installation, inspection of, and, depending on findings, corrective action(s) on, affected parts held as spare. The amount of force to the ends of the horizontal stabilizer cannot be quantified; however, fleet experience shows that repetitive pushing or pulling on the horizontal stabilizer to move the airplane on the ground can overload the rivets. Although a root cause could not be determined, due to the severity of separation of a horizontal stabilizer, EASA determined that the corrective PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 actions should be required for other airplanes of the same type design. Pilatus Aircraft Ltd. had previously considered the small size of the original ‘‘DO NOT PUSH’’ markings and the significant chance of the markings being over-sprayed during a respray. As a result, Pilatus Aircraft Ltd. issued a service bulletin to specify replacing the smaller markings with new, larger placards. The FAA proposes to require these placards in the NPRM. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–1058. Related Service Information Under 1 CFR Part 51 Pilatus Aircraft Ltd. has issued PC–6 Service Bulletin No. 55–004, dated July 2, 2018. The service information contains procedures for inspecting the left-hand and right-hand horizontal stabilizer hinge bracket assemblies and, if any discrepancies are found, repairing or replacing any damaged rivets and screws. Pilatus Aircraft Ltd. has also issued PC–6 Service Bulletin No. 55– 002, Revision. No. 1, dated February 18, 2016. This service information contains procedures for inspecting and repairing the horizontal stabilizer attachment hardware and installing four ‘‘DO NOT PUSH’’ placards. 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 and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. We have reviewed the MCAI and, in general, agree with the substance. The MCAI AD does not require installing ‘‘DO NOT PUSH’’ placards. We have added that requirement to this proposed AD. Costs of Compliance We estimate that this proposed AD would affect 30 products of U.S. registry. We also estimate that it would take about 9 work-hours per product to E:\FR\FM\26DEP1.SGM 26DEP1 amozie on DSK3GDR082PROD with PROPOSALS1 Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Proposed Rules comply with the inspection and placard requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $200 per product. Based on these figures, we estimate the cost of the proposed inspection and placard requirements on U.S. operators to be $28,950, or $965 per product. In addition, we estimate the following to do any necessary follow-on actions: Each rivet replacement would take 2 work-hours, fastener replacement would take 3 work-hours, one hinge bracket assembly replacement would take 9 work-hours, and two hinge bracket assembly replacements would take 15 work-hours. The total estimated cost of parts would be $10,000. We have no way of determining the number of products that may need replacement. Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to small airplanes, gliders, balloons, airships, domestic business jet transport airplanes, and associated appliances to the Director of the Policy and Innovation Division. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national VerDate Sep<11>2014 17:37 Dec 21, 2018 Jkt 247001 List of Subjects in 14 CFR Part 39 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): ■ Pilatus Aircraft Ltd.: Docket No. FAA–2018– 1058; Product Identifier 2018–CE–051– AD. (a) Comments Due Date We must receive comments by February 11, 2019. (b) Affected ADs None. (c) Applicability This AD applies to Pilatus Aircraft Ltd. Model PC–6, PC–6/350, PC–6/350–H1, PC–6/ 350–H2, PC–6/A, PC–6/A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/B2–H2, PC– 6/B2–H4, PC–6/C–H2, PC–6/C1–H2, PC–6– H1, PC–6–H2 airplanes, all serial numbers, certificated in any category. Note 1 to paragraph (c): These airplanes may also be identified as Fairchild Republic Company airplanes, Fairchild Industries airplanes, Fairchild Heli Porter airplanes, or Fairchild-Hiller Corporation airplanes. (d) Subject Air Transport Association of America (ATA) Code 55: Stabilizers. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 66177 (e) Reason This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as sheared or missing rivets on the horizontal stabilizer hinge bracket assemblies. We are issuing this AD to prevent failure of the primary horizontal stabilizer load path, which could lead to separation of the horizontal stabilizer and result in loss of control of the airplane. (f) Actions and Compliance Unless already done, do the following actions in paragraphs (f)(1) and (2). (1) Within the next 100 hours time-inservice after the effective date of this AD or within the next 12 months after the effective date of this AD, whichever occurs first: (i) Inspect the left-hand and the right-hand horizontal stabilizer hinge bracket assemblies for cracks, loose screws and rivets, sheared rivets, missing rivets, and looseness of the electrical bonding strap, and inspect the top and bottom screws at each hinge bracket. Repair or replace any parts with discrepancies before further flight. You must do the actions required by this paragraph by following sections C through G of the Accomplishment Instructions—Part 1—On Aircraft in Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 55–004, dated July 2, 2018. (ii) Install four ‘‘DO NOT PUSH’’ placards, part number 110.71.06.847 or 110.71.06.848, on the horizontal stabilizer by following section G of the Accomplishment Instructions—Aircraft in Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 55–002, Revision. No. 1, dated February 18, 2016. (2) After the effective date of this AD, do not install a horizontal stabilizer on any airplane unless it has been inspected as specified in paragraph (f)(1)(i) of this AD and found to be free of discrepancies or all discrepancies have been repaired or replaced. (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Small Airplane Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329–4090; email: doug.rudolph@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must instead be accomplished using a method approved by the Manager, Small Airplane Standards Branch, FAA, or the European Aviation Safety Agency (EASA). E:\FR\FM\26DEP1.SGM 26DEP1 66178 Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Proposed Rules (h) Related Information Refer to MCAI European Aviation Safety Agency AD No. 2018–0217, dated October 10, 2018, for related information. You may examine the MCAI on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018–1058. For service information related to 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. You may review this referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued in Kansas City, Missouri, on December 17, 2018. Melvin J. Johnson, Aircraft Certification Service, Deputy Director, Policy and Innovation Division, AIR–601. [FR Doc. 2018–27899 Filed 12–21–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–1012; Product Identifier 2018–NM–132–AD] RIN 2120–AA64 Examining the AD Docket Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This proposed AD was prompted by reports of uncommanded movements of the Captain’s and First Officer’s seats. This proposed AD would require an identification of the part number, and if applicable the serial number, of the Captain’s and First Officer’s seats, and do applicable on-condition actions for affected seats. This proposed AD would also require a one-time detailed inspection and repetitive checks of the horizontal movement system of the Captain’s and First Officer’s seats and applicable on-condition actions. This proposed AD would also provide an optional terminating action for the repetitive checks of the horizontal movement system. We are proposing this AD to address the unsafe condition on these products. amozie on DSK3GDR082PROD with PROPOSALS1 SUMMARY: VerDate Sep<11>2014 17:37 Dec 21, 2018 We must receive comments on this proposed AD by February 11, 2019. 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: 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 Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https:// www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018– 1012. DATES: Jkt 247001 You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 1012; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Brandon Lucero, Aerospace Engineer, Cabin Safety and Environmental Systems Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206– 231–3569; email: Brandon.Lucero@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 section. Include ‘‘Docket No. FAA– 2018–1012; Product Identifier 2018– NM–132–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. We will post all comments we receive, without change, to 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 proposed AD. Discussion We have received reports indicating that there have been uncommanded movements of the Captain’s and First Officer’s seats. A Model 747 operator reported that during a takeoff, the First Officer’s seat unlocked from its seat tracks and moved aft. The First Officer was unable to control the airplane and the Captain took over the controls to avoid a rejected takeoff. The unlocking of the seat from the seat tracks was caused by actuator damage, which was a result of incorrect adjustment of the seat’s manual release lever cable, which allowed the clutch mechanism to only partially engage. Captain’s and First Officer’s seats having the same part numbers are installed on both Model 747 and Model 777 airplanes. We are considering additional rulemaking to address the unsafe condition for Model 747 airplanes. In addition, a Model 777 operator reported that the Captain’s seat could not be locked in position after an adjustment to the horizontal seat position in flight. The seat became unlocked from the track and moved freely forward and aft. Control was given to the First Officer for approach and landing. The results of an inspection revealed that the horizontal actuator output shaft had broken. When a horizontal actuator output shaft breaks, the pilot cannot prevent seat movement in a forward and aft direction and cannot lock the seat in position. A broken horizontal actuator output shaft is the result of high loads, that exceed the design limits, caused by a stalled motor that can occur due to high mechanical resistance to motion during powered operation of the seat. Foreign object debris (FOD) in the seat tracks is another condition that can result in a stalled motor and cause the horizontal actuator output shaft to break. An uncommanded seat movement during a critical part of a flight, such as takeoff or landing, could cause a flight E:\FR\FM\26DEP1.SGM 26DEP1

Agencies

[Federal Register Volume 83, Number 246 (Wednesday, December 26, 2018)]
[Proposed Rules]
[Pages 66175-66178]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-27899]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-1058; Product Identifier 2018-CE-051-AD]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Pilatus Aircraft Ltd. Model PC-6, PC-6/350, PC-6/350-H1, PC-6/350-H2, 
PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/
B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-6-H1, and PC-6-H2 airplanes. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by an aviation authority of another country to 
identify

[[Page 66176]]

and correct an unsafe condition on an aviation product. The MCAI 
describes the unsafe condition as sheared or missing rivets on the 
horizontal stabilizer hinge bracket assemblies. We are issuing this 
proposed AD to require actions to address the unsafe condition on these 
products.

DATES: We must receive comments on this proposed AD by February 11, 
2019.

ADDRESSES: You may send comments 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 proposed 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: aircraft.com">techsupport@pilatus-aircraft.com; internet: http://
www.pilatus-aircraft.com. You may review this referenced service 
information at the FAA, Policy and Innovation Division, 901 Locust, 
Kansas City, Missouri 64106. For information on the availability of 
this material at the FAA, call (816) 329-4148.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
1058; 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 proposed AD, the regulatory evaluation, any comments received, and 
other information. The street address for Docket Operations (telephone 
(800) 647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; email: 
doug.rudolph@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2018-1058; 
Product Identifier 2018-CE-051-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD because of those comments.
    We will post all comments we receive, without change, to http://regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No. 2018-0217, dated October 10, 2018 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    During a routine inspection, the rivets of the hinge bracket 
assemblies on a Pilatus PC-6 were found to be sheared or missing. 
Investigation results identified that this was most likely due to 
application of too much force to the ends of the horizontal 
stabilizer during ground handling.
    This condition, if not detected and corrected, could lead to 
failure of the primary horizontal stabilizer load path and 
consequent separation of the horizontal stabilizer, possibly 
resulting in loss of control of the aeroplane.
    To address this potential unsafe condition, Pilatus Aircraft Ltd 
issued the SB [service bulletin] to provide applicable inspection 
instructions.
    For the reasons described above, this [EASA] AD requires a one-
time inspection of the affected parts and the horizontal stabilizer 
front spar attachment area and, depending on findings, 
accomplishment of applicable corrective action(s). This [EASA] AD 
also requires, before installation, inspection of, and, depending on 
findings, corrective action(s) on, affected parts held as spare.

    The amount of force to the ends of the horizontal stabilizer cannot 
be quantified; however, fleet experience shows that repetitive pushing 
or pulling on the horizontal stabilizer to move the airplane on the 
ground can overload the rivets. Although a root cause could not be 
determined, due to the severity of separation of a horizontal 
stabilizer, EASA determined that the corrective actions should be 
required for other airplanes of the same type design.
    Pilatus Aircraft Ltd. had previously considered the small size of 
the original ``DO NOT PUSH'' markings and the significant chance of the 
markings being over-sprayed during a respray. As a result, Pilatus 
Aircraft Ltd. issued a service bulletin to specify replacing the 
smaller markings with new, larger placards. The FAA proposes to require 
these placards in the NPRM.
    You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
1058.

Related Service Information Under 1 CFR Part 51

    Pilatus Aircraft Ltd. has issued PC-6 Service Bulletin No. 55-004, 
dated July 2, 2018. The service information contains procedures for 
inspecting the left-hand and right-hand horizontal stabilizer hinge 
bracket assemblies and, if any discrepancies are found, repairing or 
replacing any damaged rivets and screws. Pilatus Aircraft Ltd. has also 
issued PC-6 Service Bulletin No. 55-002, Revision. No. 1, dated 
February 18, 2016. This service information contains procedures for 
inspecting and repairing the horizontal stabilizer attachment hardware 
and installing four ``DO NOT PUSH'' placards. 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 and Requirements of the Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are proposing this AD because 
we evaluated all information and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design.
    We have reviewed the MCAI and, in general, agree with the 
substance. The MCAI AD does not require installing ``DO NOT PUSH'' 
placards. We have added that requirement to this proposed AD.

Costs of Compliance

    We estimate that this proposed AD would affect 30 products of U.S. 
registry. We also estimate that it would take about 9 work-hours per 
product to

[[Page 66177]]

comply with the inspection and placard requirements of this proposed 
AD. The average labor rate is $85 per work-hour. Required parts would 
cost about $200 per product.
    Based on these figures, we estimate the cost of the proposed 
inspection and placard requirements on U.S. operators to be $28,950, or 
$965 per product.
    In addition, we estimate the following to do any necessary follow-
on actions: Each rivet replacement would take 2 work-hours, fastener 
replacement would take 3 work-hours, one hinge bracket assembly 
replacement would take 9 work-hours, and two hinge bracket assembly 
replacements would take 15 work-hours. The total estimated cost of 
parts would be $10,000. We have no way of determining the number of 
products that may need 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 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to small airplanes, gliders, 
balloons, airships, domestic business jet transport airplanes, and 
associated appliances to the Director of the Policy and Innovation 
Division.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

Pilatus Aircraft Ltd.: Docket No. FAA-2018-1058; Product Identifier 
2018-CE-051-AD.

(a) Comments Due Date

    We must receive comments by February 11, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Pilatus Aircraft Ltd. Model PC-6, PC-6/350, 
PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, 
PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-6-H1, 
PC-6-H2 airplanes, all serial numbers, certificated in any category.

    Note 1 to paragraph (c): These airplanes may also be identified 
as Fairchild Republic Company airplanes, Fairchild Industries 
airplanes, Fairchild Heli Porter airplanes, or Fairchild-Hiller 
Corporation airplanes.

(d) Subject

    Air Transport Association of America (ATA) Code 55: Stabilizers.

(e) Reason

    This AD was prompted by mandatory continuing airworthiness 
information (MCAI) originated by an aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. The MCAI describes the unsafe condition as sheared or 
missing rivets on the horizontal stabilizer hinge bracket 
assemblies. We are issuing this AD to prevent failure of the primary 
horizontal stabilizer load path, which could lead to separation of 
the horizontal stabilizer and result in loss of control of the 
airplane.

(f) Actions and Compliance

    Unless already done, do the following actions in paragraphs 
(f)(1) and (2).
    (1) Within the next 100 hours time-in-service after the 
effective date of this AD or within the next 12 months after the 
effective date of this AD, whichever occurs first:
    (i) Inspect the left-hand and the right-hand horizontal 
stabilizer hinge bracket assemblies for cracks, loose screws and 
rivets, sheared rivets, missing rivets, and looseness of the 
electrical bonding strap, and inspect the top and bottom screws at 
each hinge bracket. Repair or replace any parts with discrepancies 
before further flight. You must do the actions required by this 
paragraph by following sections C through G of the Accomplishment 
Instructions--Part 1--On Aircraft in Pilatus Aircraft Ltd. PC-6 
Service Bulletin No. 55-004, dated July 2, 2018.
    (ii) Install four ``DO NOT PUSH'' placards, part number 
110.71.06.847 or 110.71.06.848, on the horizontal stabilizer by 
following section G of the Accomplishment Instructions--Aircraft in 
Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 55-002, Revision. 
No. 1, dated February 18, 2016.
    (2) After the effective date of this AD, do not install a 
horizontal stabilizer on any airplane unless it has been inspected 
as specified in paragraph (f)(1)(i) of this AD and found to be free 
of discrepancies or all discrepancies have been repaired or 
replaced.

(g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Small Airplane Standards Branch, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. Send information to ATTN: Doug Rudolph, Aerospace Engineer, 
FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas 
City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-
4090; email: doug.rudolph@faa.gov. Before using any approved AMOC on 
any airplane to which the AMOC applies, notify your appropriate 
principal inspector (PI) in the FAA Flight Standards District Office 
(FSDO), or lacking a PI, your local FSDO.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must 
instead be accomplished using a method approved by the Manager, 
Small Airplane Standards Branch, FAA, or the European Aviation 
Safety Agency (EASA).

[[Page 66178]]

(h) Related Information

    Refer to MCAI European Aviation Safety Agency AD No. 2018-0217, 
dated October 10, 2018, for related information. You may examine the 
MCAI on the internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2018-1058. For service information 
related to 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: 
aircraft.com">techsupport@pilatus-aircraft.com; internet: http://www.pilatus-
aircraft.com. You may review this referenced service information at 
the FAA, Policy and Innovation Division, 901 Locust, Kansas City, 
Missouri 64106. For information on the availability of this material 
at the FAA, call (816) 329-4148.

    Issued in Kansas City, Missouri, on December 17, 2018.
Melvin J. Johnson,
Aircraft Certification Service, Deputy Director, Policy and Innovation 
Division, AIR-601.
[FR Doc. 2018-27899 Filed 12-21-18; 8:45 am]
 BILLING CODE 4910-13-P