Airworthiness Directives; Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) Airplanes, 36675-36678 [2014-15246]

Download as PDF Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules (2) Do detailed and eddy current inspections of the frame at stations 328, 344, and 360 for cracking or a severed frame web; and external detailed and eddy current inspections of the fuselage skin for cracking. (k) Group 7 Airplanes: Repetitive Inspections, Related Investigative Actions, and Corrective Actions at Station 328 For airplanes identified as Group 7 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: At the applicable time specified in Table 6 of Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (m)(1) of this AD, do a detailed inspection of the frame at station 328 for cracking or a severed frame web; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in this paragraph thereafter at the applicable time and intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. Doing the repair of the frame at station 328, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD, terminates the repetitive inspection requirements of this paragraph. emcdonald on DSK67QTVN1PROD with PROPOSALS (l) Groups 2 Through 5 Airplanes: Repetitive Inspections, Related Investigative Actions, and Corrective Actions at Station 380 For airplanes identified as Groups 2 through 5 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: At the applicable time specified in Tables 9 and 10 of Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (m)(1) of this AD, do detailed and eddy current inspections of the frame at station 380 for cracking or a severed frame web; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspections specified in this paragraph thereafter at the applicable time and intervals specified in Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. (m) Exceptions to Service Information (1) Where Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, specifies a compliance time after the ‘‘original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, specifies to contact Boeing VerDate Mar<15>2010 17:59 Jun 27, 2014 Jkt 232001 for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (n) Post-Repair Inspections and PostModification Inspections The post-repair and post-modification inspections specified in Tables 13 through 15 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, are not required by this AD. Note 1 to paragraph (n) of this AD: The post-repair and post-modification inspections specified in Tables 13 through 15 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, may be used in support of compliance with section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, are not required by this AD. (o) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (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 (p)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (p) Related Information (1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6450; fax: 425–917–6590; email: alan.pohl@faa.gov. (2) For service information identified in this AD, 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 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 36675 information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on June 19, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–15251 Filed 6–27–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0345; Directorate Identifier 2013–NM–230–AD] RIN 2120–AA64 Airworthiness Directives; Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400, 400A, 400T, and MU–300 airplanes. This proposed AD was prompted by a report of a failure of the Acme nut threads in a pitch trim actuator (PTA). This proposed AD would require an inspection to determine if PTAs having a certain serial number and part number are installed, and replacement if they are installed. This proposed AD would also require repetitive replacements of PTAs with new PTAs or certain overhauled PTAs. We are proposing this AD to prevent failure of the Acme nut threads in the PTA, which could lead to loss of control of pitch trim and reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by August 29, 2014. 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 SUMMARY: E:\FR\FM\30JNP1.SGM 30JNP1 36676 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 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 proposed AD, contact Beechcraft Corporation, TMDC, P.O. Box 85, Wichita, KS 67201–0085; telephone 316–676–8238; fax 316–671–2540; email tmdc@beechcraft.com; Internet http:// pubs.beechcraft.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. 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–2014– 0345; 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 proposed 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: Ann Johnson, Aerospace Engineer, Systems and Propulsion Branch, ACE–116W, FAA, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, KS 67209; phone: (316) 946–4105; fax: (316) 946–4107; email: Ann.Johnson@ faa.gov. having specific serial numbers listed in the service bulletin. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2014–0345; Directorate Identifier 2013– NM–230–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:// 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 a report of a failure of the Acme nut threads in a PTA, due to accelerated thread wear on the Acme nut that mates with the jackscrew. This condition, if not corrected, could result in failure of the Acme nut threads in the PTA, which could lead to loss of control of pitch trim and reduced controllability of the airplane. Relevant Service Information We reviewed Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012. This service bulletin describes procedures for an inspection to determine if PTAs having a certain serial number and part number are installed, and replacing those PTAs FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between This Proposed AD and the Service Information.’’ Differences Between This Proposed AD and the Service Information Although Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012, does not require repetitive replacements, this proposed AD would require repetitive replacements of PTAs with new PTAs or with overhauled PTAs having an Acme nut and jackscrew replaced with a new Acme nut and jackscrew every 1,800 flight hours or at the next PTA overhaul, whichever occurs first. While the effectivity of Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012, does not include Model MU–300 airplanes, those airplanes are included in the applicability of this proposed AD since the affected PTAs can also be used on these airplanes. Costs of Compliance We estimate that this proposed AD affects 735 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Identification of serial/part numbers (735 airplanes). Replacement of PTA (26 airplanes). emcdonald on DSK67QTVN1PROD with PROPOSALS Repetitive replacement of jackscrew and Acme nut on PTAs (735 airplanes). 1 work-hour × $85 per hour = $85. 10 work-hours × $85 per hour = $850 per replacement. 10 work-hours × $85 per hour = $850 per replacement. According to the manufacturer, the costs of this proposed AD associated with Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012, may be covered under warranty, thereby reducing the cost impact on affected owners/operators. We do not VerDate Mar<15>2010 Parts cost Cost per product $0 ...................................... $85 .................................... $62,475. $17,334 per replacement .. $18,184 per replacement .. $472,784 per replacement. $17,334 per replacement .. $18,184 per replacement .. $13,365,240 per replacement. Labor cost 17:59 Jun 27, 2014 Jkt 232001 control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. The costs of the repetitive replacement are not covered under warranty. However, the PTA manufacturer states that it is already replacing the Acme nut PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 Cost on U.S. operators and jackscrew at every overhaul, so the owners/operators should not see a cost increase due to this repetitive replacement requirement. E:\FR\FM\30JNP1.SGM 30JNP1 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed 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 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 proposed regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings 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. emcdonald on DSK67QTVN1PROD with PROPOSALS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. VerDate Mar<15>2010 17:59 Jun 27, 2014 Jkt 232001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation): Docket No. FAA–2014–0345; Directorate Identifier 2013–NM–230–AD. (a) Comments Due Date We must receive comments by August 29, 2014. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) airplanes identified in paragraphs (c)(1)(i), (c)(1)(ii), and (c)(1)(iii) of this AD. (i) Model 400 Beechjet airplanes having serial numbers RJ–1 through RJ–65, inclusive. (ii) Model 400A Beechjet airplanes having serial numbers RK–1 through RK–604, inclusive. (iii) Model 400T Beechjet airplanes having serial numbers TT–1 through TT–180, inclusive, and TX–1 through TX–13, inclusive. (2) Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Mitsubishi Heavy Industries, Inc. Ltd.) Model MU–300 airplanes, having serial numbers A003SA through A093SA, inclusive. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Unsafe Condition This AD was prompted by a report of a failure of the Acme nut threads in a pitch trim actuator (PTA). We are issuing this AD to prevent failure of the Acme nut threads in the PTA, which could lead to loss of control of pitch trim and reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Determination of Serial Number and Part Number Within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first, inspect to determine the serial number and part number of the PTA, in accordance with the Accomplishment Instructions of Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012. A review of manufacturer delivery and operator maintenance records is acceptable, in lieu of the inspection, if the serial number PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 36677 and part number of the PTA can be conclusively determined from that review. (h) Replacement If any serial number and part number found during an inspection required by paragraph (g) of this AD is one listed in Table 1 or Table 2 of Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012: Within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first, replace the PTA with a serviceable PTA or an overhauled PTA having an Acme nut and jackscrew replaced with a new Acme nut and jackscrew, in accordance with the Accomplishment Instructions of Hawker Beechcraft Mandatory Service Bulletin 27– 4100, dated March 2012. (i) Repetitive Replacements Within 1,800 flight hours after the effective date of this AD, or at the next PTA overhaul, whichever occurs first, replace the PTA with a new PTA or an overhauled PTA having the Acme nut and jackscrew replaced with a new Acme nut and jackscrew, in accordance with sections 3.A.(2), (3), and (5) through (10) of Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012. Repeat the replacement thereafter at intervals not to exceed 1,800 flight hours, or at every PTA overhaul, whichever occurs first. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Wichita Aircraft Certification Office (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 (k)(1) of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (k) Related Information (1) For more information about this AD, contact Ann Johnson, Aerospace Engineer, Systems and Propulsion Branch, ACE–116W, FAA, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, MidContinent Airport, Wichita, KS 67209; phone: (316) 946–4105; fax: (316) 946–4107; email: Ann.Johnson@faa.gov. (2) For service information identified in this AD, contact Beechcraft Corporation, TMDC, P.O. Box 85, Wichita, KS 67201– 0085; telephone 316–676–8238; fax 316–671– 2540; email tmdc@beechcraft.com; Internet http://pubs.beechcraft.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. E:\FR\FM\30JNP1.SGM 30JNP1 36678 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules Issued in Renton, Washington, on June 10, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–15246 Filed 6–27–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0426; Directorate Identifier 2013–NM–231–AD] RIN 2120–AA64 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 certain The Boeing Company Model 767 and 777 airplanes. This proposed AD was prompted by reports of uncommanded door closure of the large lower lobe cargo door. This proposed AD would require inspecting for part numbers and serial numbers of the rotary actuators of the large forward and aft lower lobe cargo doors, as applicable, and corrective action if necessary. We are proposing this AD to detect and correct rotary actuators made with a material having poor actuator gear wear characteristics, which could result in failure of the rotary actuators for the large forward or aft lower lobe cargo door and subsequent uncommanded door closure, which could possibly result in injury to people on the ground. DATES: We must receive comments on this proposed AD by August 14, 2014. 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 Boeing service information identified in this proposed AD, contact emcdonald on DSK67QTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 17:59 Jun 27, 2014 Jkt 232001 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. For Eaton service information identified in this proposed AD, contact Eaton Corporation, Aerospace Operations, 3 Park Plaza, Suite 1200, Irvine, CA 92614; telephone 949–253–2100; fax 949–253–2111; Internet http:// www.eaton.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. 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–2014– 0426; 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 proposed 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: Susan Monroe, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6457; fax: 425–917–6590; email: susan.l.monroe@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2014–0426; Directorate Identifier 2013– NM–231–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:// www.regulations.gov, including any personal information you provide. We PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We received reports of uncommanded door closure of the large lower lobe cargo door. One incident occurred while the door was being opened, a second one while the door was stationary in the open position, and the third incident occurred as the door was being closed. It was determined that all of the doors’ rotary actuators had failed (two actuators per door). The three incidents occurred on Model 767 airplanes, but the same rotary actuator part numbers are also used on the large lower lobe cargo doors installed on the Model 777 airplanes. Examination of five of the failed rotary actuators found significant wear in the gear box and failure of the first stage input sun gear set. The sixth failed rotary actuator had a failed thirdstage input sun gear from an overload condition. All three affected airplanes had between 12,500 and 13,500 total flight cycles. The failed actuators were manufactured with Nitralloy 135M steel between August 1994 and December 2000. Actuators manufactured before or after that timeframe were made with 9310 steel. The rotary actuators made from 9310 steel material are considered safe. This condition, if not corrected, could result in failure of the rotary actuators for the large lower lobe cargo door, and subsequent uncommanded door closures, which could possibly result in injury to people on the ground. Relevant Service Information We reviewed Boeing Service Bulletins 767–52A0100, Revision 2, dated September 26, 2013; and 777–52–0053, Revision 1, dated September 26, 2013. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0426. Boeing Service Bulletins 767– 52A0100, Revision 2, dated September 26, 2013; and 777–52–0053, Revision 1, dated September 26, 2013; refer to Eaton Service Bulletin 692D100–52–4, Revision 2, dated August 1, 2013, which provides serial number information and certain corrective actions (rework of certain rotary actuators or reidentification of certain other rotary actuators). FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or E:\FR\FM\30JNP1.SGM 30JNP1

Agencies

[Federal Register Volume 79, Number 125 (Monday, June 30, 2014)]
[Proposed Rules]
[Pages 36675-36678]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-15246]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0345; Directorate Identifier 2013-NM-230-AD]
RIN 2120-AA64


Airworthiness Directives; Beechcraft Corporation (Type 
Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon 
Aircraft Company; Beech Aircraft Corporation) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Beechcraft Corporation (Type Certificate Previously Held by 
Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech 
Aircraft Corporation) Model 400, 400A, 400T, and MU-300 airplanes. This 
proposed AD was prompted by a report of a failure of the Acme nut 
threads in a pitch trim actuator (PTA). This proposed AD would require 
an inspection to determine if PTAs having a certain serial number and 
part number are installed, and replacement if they are installed. This 
proposed AD would also require repetitive replacements of PTAs with new 
PTAs or certain overhauled PTAs. We are proposing this AD to prevent 
failure of the Acme nut threads in the PTA, which could lead to loss of 
control of pitch trim and reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by August 29, 2014.

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

[[Page 36676]]

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 proposed AD, contact 
Beechcraft Corporation, TMDC, P.O. Box 85, Wichita, KS 67201-0085; 
telephone 316-676-8238; fax 316-671-2540; email tmdc@beechcraft.com; 
Internet http://pubs.beechcraft.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.

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-2014-
0345; 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 proposed 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: Ann Johnson, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft 
Certification Office (ACO), 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, KS 67209; phone: (316) 946-4105; fax: (316) 946-4107; 
email: Ann.Johnson@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2014-0345; 
Directorate Identifier 2013-NM-230-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://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 a report of a failure of the Acme nut threads in a 
PTA, due to accelerated thread wear on the Acme nut that mates with the 
jackscrew. This condition, if not corrected, could result in failure of 
the Acme nut threads in the PTA, which could lead to loss of control of 
pitch trim and reduced controllability of the airplane.

Relevant Service Information

    We reviewed Hawker Beechcraft Mandatory Service Bulletin 27-4100, 
dated March 2012. This service bulletin describes procedures for an 
inspection to determine if PTAs having a certain serial number and part 
number are installed, and replacing those PTAs having specific serial 
numbers listed in the service bulletin.

FAA's Determination

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

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between This Proposed AD and the Service 
Information.''

Differences Between This Proposed AD and the Service Information

    Although Hawker Beechcraft Mandatory Service Bulletin 27-4100, 
dated March 2012, does not require repetitive replacements, this 
proposed AD would require repetitive replacements of PTAs with new PTAs 
or with overhauled PTAs having an Acme nut and jackscrew replaced with 
a new Acme nut and jackscrew every 1,800 flight hours or at the next 
PTA overhaul, whichever occurs first.
    While the effectivity of Hawker Beechcraft Mandatory Service 
Bulletin 27-4100, dated March 2012, does not include Model MU-300 
airplanes, those airplanes are included in the applicability of this 
proposed AD since the affected PTAs can also be used on these 
airplanes.

Costs of Compliance

    We estimate that this proposed AD affects 735 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Identification of serial/part     1 work-hour x $85   $0................  $85...............  $62,475.
 numbers (735 airplanes).          per hour = $85.
Replacement of PTA (26            10 work-hours x     $17,334 per         $18,184 per         $472,784 per
 airplanes).                       $85 per hour =      replacement.        replacement.        replacement.
                                   $850 per
                                   replacement.
Repetitive replacement of         10 work-hours x     $17,334 per         $18,184 per         $13,365,240 per
 jackscrew and Acme nut on PTAs    $85 per hour =      replacement.        replacement.        replacement.
 (735 airplanes).                  $850 per
                                   replacement.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, the costs of this proposed AD 
associated with Hawker Beechcraft Mandatory Service Bulletin 27-4100, 
dated March 2012, may be covered under warranty, thereby reducing the 
cost impact on affected owners/operators. We do not control warranty 
coverage for affected individuals. As a result, we have included all 
costs in our cost estimate. The costs of the repetitive replacement are 
not covered under warranty. However, the PTA manufacturer states that 
it is already replacing the Acme nut and jackscrew at every overhaul, 
so the owners/operators should not see a cost increase due to this 
repetitive replacement requirement.

[[Page 36677]]

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 proposed regulation is 
within the scope of that authority because it addresses an unsafe 
condition that is likely to exist or develop on products identified in 
this rulemaking action.

Regulatory Findings

    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):

Beechcraft Corporation (Type Certificate Previously Held by Hawker 
Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft 
Corporation): Docket No. FAA-2014-0345; Directorate Identifier 2013-
NM-230-AD.

(a) Comments Due Date

    We must receive comments by August 29, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Beechcraft Corporation (Type Certificate Previously Held by 
Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech 
Aircraft Corporation) airplanes identified in paragraphs (c)(1)(i), 
(c)(1)(ii), and (c)(1)(iii) of this AD.
    (i) Model 400 Beechjet airplanes having serial numbers RJ-1 
through RJ-65, inclusive.
    (ii) Model 400A Beechjet airplanes having serial numbers RK-1 
through RK-604, inclusive.
    (iii) Model 400T Beechjet airplanes having serial numbers TT-1 
through TT-180, inclusive, and TX-1 through TX-13, inclusive.
    (2) Beechcraft Corporation (Type Certificate Previously Held by 
Hawker Beechcraft Corporation; Raytheon Aircraft Company; Mitsubishi 
Heavy Industries, Inc. Ltd.) Model MU-300 airplanes, having serial 
numbers A003SA through A093SA, inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Unsafe Condition

    This AD was prompted by a report of a failure of the Acme nut 
threads in a pitch trim actuator (PTA). We are issuing this AD to 
prevent failure of the Acme nut threads in the PTA, which could lead 
to loss of control of pitch trim and reduced controllability of the 
airplane.

(f) Compliance

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

(g) Determination of Serial Number and Part Number

    Within 200 flight hours or 6 months after the effective date of 
this AD, whichever occurs first, inspect to determine the serial 
number and part number of the PTA, in accordance with the 
Accomplishment Instructions of Hawker Beechcraft Mandatory Service 
Bulletin 27-4100, dated March 2012. A review of manufacturer 
delivery and operator maintenance records is acceptable, in lieu of 
the inspection, if the serial number and part number of the PTA can 
be conclusively determined from that review.

(h) Replacement

    If any serial number and part number found during an inspection 
required by paragraph (g) of this AD is one listed in Table 1 or 
Table 2 of Hawker Beechcraft Mandatory Service Bulletin 27-4100, 
dated March 2012: Within 200 flight hours or 6 months after the 
effective date of this AD, whichever occurs first, replace the PTA 
with a serviceable PTA or an overhauled PTA having an Acme nut and 
jackscrew replaced with a new Acme nut and jackscrew, in accordance 
with the Accomplishment Instructions of Hawker Beechcraft Mandatory 
Service Bulletin 27-4100, dated March 2012.

(i) Repetitive Replacements

    Within 1,800 flight hours after the effective date of this AD, 
or at the next PTA overhaul, whichever occurs first, replace the PTA 
with a new PTA or an overhauled PTA having the Acme nut and 
jackscrew replaced with a new Acme nut and jackscrew, in accordance 
with sections 3.A.(2), (3), and (5) through (10) of Hawker 
Beechcraft Mandatory Service Bulletin 27-4100, dated March 2012. 
Repeat the replacement thereafter at intervals not to exceed 1,800 
flight hours, or at every PTA overhaul, whichever occurs first.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Wichita Aircraft Certification Office (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 (k)(1) of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(k) Related Information

    (1) For more information about this AD, contact Ann Johnson, 
Aerospace Engineer, Systems and Propulsion Branch, ACE-116W, FAA, 
Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 
100, Mid-Continent Airport, Wichita, KS 67209; phone: (316) 946-
4105; fax: (316) 946-4107; email: Ann.Johnson@faa.gov.
    (2) For service information identified in this AD, contact 
Beechcraft Corporation, TMDC, P.O. Box 85, Wichita, KS 67201-0085; 
telephone 316-676-8238; fax 316-671-2540; email tmdc@beechcraft.com; 
Internet http://pubs.beechcraft.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.


[[Page 36678]]


    Issued in Renton, Washington, on June 10, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-15246 Filed 6-27-14; 8:45 am]
BILLING CODE 4910-13-P