Airworthiness Directives; British Aerospace Regional Aircraft Airplanes, 10973-10976 [2017-02771]

Download as PDF Federal Register / Vol. 82, No. 32 / Friday, February 17, 2017 / Proposed Rules 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): ■ Romtex Anjou Aeronautique (Romtex) Torso Restraint Systems: Docket No. FAA– 2017–0068; Directorate Identifier 2014– SW–076–AD. (a) Applicability This AD applies to Romtex torso restraint systems (restraint systems) with a rotary buckle sub-assembly (buckle assembly) with a part number and serial number as listed in the Effectivity, paragraph 1.2, of Romtex Service Bulletin No. 358SB–14–101, Revision 1, dated December 12, 2014. These restraint systems are installed on, but not limited to, Airbus Helicopters Model AS350B2, AS350B3, EC130B4, EC130T2, and AS355NP helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a broken buckle knob. This condition could result in a restraint system strap failing to release from the buckle, preventing occupants from exiting the helicopter during an emergency. (c) Comments Due Date We must receive comments by April 18, 2017. mstockstill on DSK3G9T082PROD with PROPOSALS (e) Required Actions (1) Within 30 hours time-in-service (TIS), inspect each restraint system for correct operation. (i) If the straps do not release from the buckle assembly, placard the seat as inoperative. Within 180 hours TIS, replace the buckle assembly with a buckle assembly not identified in paragraph (a) of this AD. (ii) If the straps release, within 180 hours TIS, replace the buckle assembly with a buckle assembly not identified in paragraph (a) of this AD. (2) Do not install a restraint system with a buckle assembly identified in paragraph (a) of this AD on any helicopter. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: David Hatfield, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5116; email 9-ASWFTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 16:56 Feb 16, 2017 Jkt 241001 (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2014–0279, dated December 19, 2014. You may view the EASA AD on the Internet at http://www.regulations.gov in the AD Docket. (h) Subject Joint Aircraft Service Component (JASC) Code: 2500 Cabin Equipment/Furnishings. Issued in Fort Worth, Texas, on January 24, 2017. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2017–02858 Filed 2–16–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0053; Directorate Identifier 2016–CE–037–AD] RIN 2120–AA64 (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. VerDate Sep<11>2014 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. Airworthiness Directives; British Aerospace Regional Aircraft 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 British Aerospace Regional Aircraft Model HP 137 Jetstream MK1, Jetstream Series 200, and Jetstream Series 3101 airplanes that would supersede AD 2014–07–07. This proposed AD results from 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 cracking of the forward main landing gear yoke pintle resulting from corrosion pits leading to stress corrosion cracking. 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 April 3, 2017. ADDRESSES: You may send comments by any of the following methods: SUMMARY: PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 10973 • 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 BAE Systems (Operations) Ltd, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; phone: +44 1292 675207, fax: +44 1292 675704; email: RApublications@baesystems.com; Internet: http:// www.jetstreamcentral.com. You may view 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. 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–2017– 0053; 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 (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 Directorate, 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–2017–0053; Directorate Identifier 2016–CE–037–AD’’ at the beginning of your comments. We specifically invite E:\FR\FM\17FEP1.SGM 17FEP1 10974 Federal Register / Vol. 82, No. 32 / Friday, February 17, 2017 / Proposed Rules 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. mstockstill on DSK3G9T082PROD with PROPOSALS Discussion On April 4, 2014, we issued AD 2014– 07–07, Amendment 39–17821 (79 FR 23897; April 29, 2014) (‘‘2014–07–07’’). That AD required actions intended to address an unsafe condition on British Aerospace Regional Aircraft Model HP 137 Jetstream MK1, Jetstream Series 200, and Jetstream Series 3101 airplanes and was based on mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. Since we issued AD 2014–07–07, additional stress corrosion cracking in the pintle housing has been found that may not be detected during the current inspection procedures. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD No.: 2016–0224, dated November 9, 2016 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Prompted by occurrences of the main landing gear (MLG) yoke pintle housing cracking, the Civil Aviation Authority (CAA) UK issued AD 003–01–86 to require repetitive inspections to detect cracks in the yoke pintle housing on MLG fitted to Jetstream 3100 aeroplanes in accordance with BAE Systems (Operations) Ltd Service Bulletin (SB) 32–A–JA851226, and, depending on findings, corrective action. After that AD was issued, an occurrence was reported of Jetstream 3100 MLG failure after landing. The subsequent investigation revealed stress corrosion cracking of the MLG yoke pintle housing to have caused this MLG failure. Furthermore, the investigation report recommended a review of the effectiveness of CAA UK AD 003–01–86 in finding cracks in the yoke pintle housing on MLG fitted to Jetstream 3100 aeroplanes. Degradation of the surface protection by abrasion can occur when the forward face of the yoke pintle rotates against the pintle bearing, which introduces corrosion pits and, consequently, stress corrosion cracking. This condition, if not detected and corrected, could lead to structural failure of the MLG, possibly resulting in loss of control of the aeroplane during take-off or landing runs. To provide protection of the affected area of the MLG assembly spigot housing, BAE VerDate Sep<11>2014 16:56 Feb 16, 2017 Jkt 241001 Systems (Operations) Ltd issued SB 32– JM7862 to provide instructions for installation of a protective washer, fitted at the forward spigot on both left hand and right hand MLG. Consequently, BAE Systems (Operations) Ltd issued SB 32–A–JA851226 Revision 05 to provide additional accomplishment instructions for a Nondestructive testing (NDT) inspection of MLG equipped with the protective washer installed in accordance with BAE Systems (Operations) Ltd SB 32–JM7862. Consequently, EASA issued AD 2013– 0208, retaining the requirements of CAA UK AD 003–01–86, which was superseded, and required implementation of revised inspection requirements, and, depending on findings, accomplishment of applicable corrective action(s). That AD also introduced an optional modification, which constituted terminating action for the inspections required by that AD. Since that AD was issued, BAE Systems (Operations) Ltd has determined that the existing inspection procedure may not be effective in identifying stress corrosion cracking in the pintle housing. Consequently BAE Systems (Operations) Ltd has published an improved inspection procedure in SB 32– A–JA851226 Revision 07. This improved inspection procedure has the ability to detect smaller corrosion pits and cracks that are proximate in size to those that will initiate stress corrosion. For the reasons described above, this AD retains the requirements of EASA AD 2013– 0208, which is superseded, and requires MLG inspections in accordance with the improved procedure. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0053. Related Service Information Under 1 CFR Part 51 British Aerospace Regional Aircraft has issued British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32– A–JA851226, Revision 7, dated May 25, 2015. The service information describes procedures for nondestructive testing (NDT) and visual inspections of the main landing gear spigot housing for cracks and repair if necessary. 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 of this NPRM. 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 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 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. Costs of Compliance We estimate that this proposed AD will affect 26 products of U.S. registry. We also estimate that it would take about 14 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $30,940, or $1,190 per product. In addition, we estimate that any necessary follow-on actions would take about 2 work-hours and require parts costing $5,000, for a cost of $5,170 per product. We have no way of determining the number of products that may need these actions. 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. 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 E:\FR\FM\17FEP1.SGM 17FEP1 Federal Register / Vol. 82, No. 32 / Friday, February 17, 2017 / Proposed Rules 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 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 Amendment 39–17821 (82 FR 23897; April 29, 2014), and adding the following new AD: ■ British Aerospace Regional Aircraft: Docket No. FAA–2017–0053; Directorate Identifier 2016–CE–037–AD. (a) Comments Due Date We must receive comments by April 3, 2017. (b) Affected ADs This AD replaces AD 2014–07–07, Amendment 39–17821 (79 FR 23897; April 29, 2014) (‘‘2014–07–07’’). (c) Applicability This AD applies to British Aerospace (Operations) Limited Model HP.137 Jetstream Mk.1, Jetstream Series 200, and Jetstream Series 3101 airplanes, all serial numbers, certificated in any category. mstockstill on DSK3G9T082PROD with PROPOSALS (d) Subject Air Transport Association of America (ATA) Code 32: Landing Gear. (e) Reason This AD was prompted by mandatory continuing airworthiness information (MCAI) issued 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 cracking of the forward main landing gear yoke pintle resulting from corrosion pits which can cause stress corrosion cracking resulting in loss of control during take-off or landing. We are issuing this AD to revise the inspection procedure to detect smaller corrosion pits and cracks that could initiate stress corrosion cracking. VerDate Sep<11>2014 16:56 Feb 16, 2017 Jkt 241001 (f) Actions and Compliance Unless already done, do the following actions specified in paragraphs (f)(1) through (11) of this AD: (1) For all airplanes: Before or at the next inspection that would have been required by AD 2014–07–07 or within the next 30 days after the effective date of this AD, whichever occurs later, and repetitively thereafter at intervals not to exceed 12 months or 1,200 main landing gear (MLG) flight cycles (FC), whichever occurs first, do a nondestructive testing (NDT) inspection of each MLG assembly cylinder attachment spigot housing following the Accomplishment Instructions in paragraph 2.B. Part A of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A–JA851226, Revision 7, dated May 25, 2015. (2) For all airplanes: Within 300 landings after a heavy or abnormal landing or 3 months after a heavy or abnormal landing, whichever occurs first, do a NDT inspection of each MLG assembly cylinder attachment spigot housing following the accomplishment instructions in paragraph 2.B. Part A of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A–JA851226, Revision 7, dated May 25, 2015. (3) For all airplanes: Within 3 months after accomplishment of the the latest NDT inspection required by paragraph (f)(1) of this AD or 300 MLG FC after accomplishment of the latest NDT inspection required by paragraph (f)(1) of this AD, whichever occurs first, and repetitively thereafter at intervals not to exceed 3 months or 300 MLG FC, whichever occurs first, do a visual inspection of each MLG following the accomplishment instructions in paragraph 2.B. Part B of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A–JA851226, Revision 7, dated May 25, 2015. These inspections start over after every repetitive NDT inspection required by paragraph (f)(1)of this AD. (4) For all airplanes with a MLG incorporating a microswitch hole: Within the next 10,600 MLG FC since new and repetitively thereafter at intervals not to exceed 1,200 MLG flight cycles, do a NDT inspection of each MLG microswitch hole following the accomplishment instructions in paragraph 2.B. Part C of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A–JA851226, Revision 7, dated May 25, 2015. (5) For all airplanes: If any discrepancy is found during any NDT inspection required in paragraphs (f)(1), (2), or (4) of this AD, before further flight, take all necessary corrective actions following the instructions in British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A–JA851226, Revision 7, dated May 25, 2015. (6) For all airplanes: If any discrepancy is found during any visual inspection required in paragraph (f)(3) of this AD, before further flight, take all necessary corrective actions following the instructions in British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A–JA851226, Revision 7, dated May 25, 2015. (7) For all airplanes: Doing all necessary corrective actions required in paragraphs (f)(5) or (6) of this AD does not constitute PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 10975 terminating action for the inspections required by this AD. (8) For all airplanes: Modification of each MLG cylinder following BAE Systems (Operations) Ltd. Service Bulletin 32– JA880340 original issue, dated January 6, 1989, constitutes terminating action for the inspections required by this AD for that MLG. (9) For all airplanes: The compliance times in paragraphs (f)(1), (2), (3), and (4) of this AD are presented in flight cycles (landings). If the total flight cycles have not been kept, multiply the total number of airplane hours time-in-service (TIS) by 0.75 to calculate the cycles. For the purposes of this AD: (i) 100 hours TIS × .75 = 75 cycles; and (ii) 1,000 hours TIS × .75 = 750 cycles. (g) Credit for Actions Done in Accordance With Previous Service Information (1) This AD allows credit for the initial inspection required in paragraph (f)(1) of this AD if done before June 3, 2014 (the effective date retained from AD 2014–07–07) following British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A– JA851226, Revision 5, dated April 30, 2013. (2) This AD allows credit for the initial inspection required in paragraph (f)(4) of this AD if done before June 3, 2014 (the effective date retained from AD 2014–07–07) following APPH Ltd. Service Bulletin 32–40, at Initial Issue dated June 21, 1989. (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, 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 Directorate, 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, a federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, E:\FR\FM\17FEP1.SGM 17FEP1 10976 Federal Register / Vol. 82, No. 32 / Friday, February 17, 2017 / Proposed Rules including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (i) Related Information Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 2016–0224, dated November 9, 2016 for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0053. For service information related to this AD, contact BAE Systems (Operations) Ltd, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; phone: +44 1292 675207, fax: +44 1292 675704; email: RApublications@baesystems.com; Internet: http://www.jetstreamcentral.com. You may review copies of the 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. Issued in Kansas City, Missouri, on January 19, 2017. Melvin Johnson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–02771 Filed 2–16–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0078; Directorate Identifier 2015–SW–026–AD] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Limited Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. This proposed AD would require adding an identification number to life-limited rod ends that do not have a serial number (S/N). The proposed actions are intended to address an unsafe condition on these products. DATES: We must receive comments on this proposed AD by April 18, 2017. mstockstill on DSK3G9T082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:56 Feb 16, 2017 Jkt 241001 You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. ADDRESSES: 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–2017– 0078 or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the Transport Canada AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed rule, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363–8023; fax (450) 433–0272; or at http://www.bellcustomer.com/files/. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. Discussion Transport Canada, which is the aviation authority for Canada, has issued AD No. CF–2015–15, dated June 25, 2015, to correct an unsafe condition for Bell Model 429 helicopters, S/Ns 57001 through 57260. Transport Canada advises that, per its regulations, lifelimited parts must be marked with their part number (P/N) and S/N. Transport Canada further states that the pylon restraint spring assembly (spring assembly) rod end P/N 427–010–210– 105 has a life limit of 5,000 hours; however, it is not serialized, causing difficulties in tracking its accumulated air time. According to Transport Canada, this condition could result in a rod end remaining in service beyond its life limit. Therefore, the Transport Canada AD requires adding identification markings on each spring assembly rod end. FAA’s Determination These helicopters have been approved by the aviation authority of Canada and are approved for operation in the United States. Pursuant to our bilateral agreement with Canada, Transport Canada, its technical representative, has notified us of the unsafe condition described in its AD. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition is likely to exist or develop on other products of the same type design. Related Service Information Under 1 CFR Part 51 Bell Helicopter has issued Alert Service Bulletin 429–15–19, dated February 26, 2015. This service information specifies procedures for permanently marking each forward and aft rod end with the S/N of the spring assembly. This service information E:\FR\FM\17FEP1.SGM 17FEP1

Agencies

[Federal Register Volume 82, Number 32 (Friday, February 17, 2017)]
[Proposed Rules]
[Pages 10973-10976]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-02771]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0053; Directorate Identifier 2016-CE-037-AD]
RIN 2120-AA64


Airworthiness Directives; British Aerospace Regional Aircraft 
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 
British Aerospace Regional Aircraft Model HP 137 Jetstream MK1, 
Jetstream Series 200, and Jetstream Series 3101 airplanes that would 
supersede AD 2014-07-07. This proposed AD results from 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 cracking of the forward main landing gear yoke pintle 
resulting from corrosion pits leading to stress corrosion cracking. 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 April 3, 2017.

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 BAE 
Systems (Operations) Ltd, Customer Information Department, Prestwick 
International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; 
phone: +44 1292 675207, fax: +44 1292 675704; email: 
RApublications@baesystems.com; Internet: http://www.jetstreamcentral.com. You may view 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.

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-2017-
0053; 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 (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 Directorate, 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-2017-0053; 
Directorate Identifier 2016-CE-037-AD'' at the beginning of your 
comments. We specifically invite

[[Page 10974]]

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

    On April 4, 2014, we issued AD 2014-07-07, Amendment 39-17821 (79 
FR 23897; April 29, 2014) (``2014-07-07''). That AD required actions 
intended to address an unsafe condition on British Aerospace Regional 
Aircraft Model HP 137 Jetstream MK1, Jetstream Series 200, and 
Jetstream Series 3101 airplanes and was based on mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority of 
another country.
    Since we issued AD 2014-07-07, additional stress corrosion cracking 
in the pintle housing has been found that may not be detected during 
the current inspection procedures.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD No.: 2016-0224, dated November 9, 2016 (referred to after this as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Prompted by occurrences of the main landing gear (MLG) yoke 
pintle housing cracking, the Civil Aviation Authority (CAA) UK 
issued AD 003-01-86 to require repetitive inspections to detect 
cracks in the yoke pintle housing on MLG fitted to Jetstream 3100 
aeroplanes in accordance with BAE Systems (Operations) Ltd Service 
Bulletin (SB) 32-A-JA851226, and, depending on findings, corrective 
action. After that AD was issued, an occurrence was reported of 
Jetstream 3100 MLG failure after landing. The subsequent 
investigation revealed stress corrosion cracking of the MLG yoke 
pintle housing to have caused this MLG failure. Furthermore, the 
investigation report recommended a review of the effectiveness of 
CAA UK AD 003-01-86 in finding cracks in the yoke pintle housing on 
MLG fitted to Jetstream 3100 aeroplanes.
    Degradation of the surface protection by abrasion can occur when 
the forward face of the yoke pintle rotates against the pintle 
bearing, which introduces corrosion pits and, consequently, stress 
corrosion cracking. This condition, if not detected and corrected, 
could lead to structural failure of the MLG, possibly resulting in 
loss of control of the aeroplane during take-off or landing runs.
    To provide protection of the affected area of the MLG assembly 
spigot housing, BAE Systems (Operations) Ltd issued SB 32-JM7862 to 
provide instructions for installation of a protective washer, fitted 
at the forward spigot on both left hand and right hand MLG. 
Consequently, BAE Systems (Operations) Ltd issued SB 32-A-JA851226 
Revision 05 to provide additional accomplishment instructions for a 
Non-destructive testing (NDT) inspection of MLG equipped with the 
protective washer installed in accordance with BAE Systems 
(Operations) Ltd SB 32-JM7862.
    Consequently, EASA issued AD 2013-0208, retaining the 
requirements of CAA UK AD 003-01-86, which was superseded, and 
required implementation of revised inspection requirements, and, 
depending on findings, accomplishment of applicable corrective 
action(s). That AD also introduced an optional modification, which 
constituted terminating action for the inspections required by that 
AD.
    Since that AD was issued, BAE Systems (Operations) Ltd has 
determined that the existing inspection procedure may not be 
effective in identifying stress corrosion cracking in the pintle 
housing. Consequently BAE Systems (Operations) Ltd has published an 
improved inspection procedure in SB 32-A-JA851226 Revision 07. This 
improved inspection procedure has the ability to detect smaller 
corrosion pits and cracks that are proximate in size to those that 
will initiate stress corrosion.
    For the reasons described above, this AD retains the 
requirements of EASA AD 2013-0208, which is superseded, and requires 
MLG inspections in accordance with the improved procedure.

You may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2017-0053.

Related Service Information Under 1 CFR Part 51

    British Aerospace Regional Aircraft has issued British Aerospace 
Jetstream Series 3100 & 3200 Service Bulletin 32-A-JA851226, Revision 
7, dated May 25, 2015. The service information describes procedures for 
nondestructive testing (NDT) and visual inspections of the main landing 
gear spigot housing for cracks and repair if necessary. 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 of this NPRM.

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.

Costs of Compliance

    We estimate that this proposed AD will affect 26 products of U.S. 
registry. We also estimate that it would take about 14 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $30,940, or $1,190 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 2 work-hours and require parts costing $5,000, for a cost of 
$5,170 per product. We have no way of determining the number of 
products that may need these actions.

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.

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

[[Page 10975]]

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 removing Amendment 39-17821 (82 FR 
23897; April 29, 2014), and adding the following new AD:

British Aerospace Regional Aircraft: Docket No. FAA-2017-0053; 
Directorate Identifier 2016-CE-037-AD.

(a) Comments Due Date

    We must receive comments by April 3, 2017.

(b) Affected ADs

    This AD replaces AD 2014-07-07, Amendment 39-17821 (79 FR 23897; 
April 29, 2014) (``2014-07-07'').

(c) Applicability

    This AD applies to British Aerospace (Operations) Limited Model 
HP.137 Jetstream Mk.1, Jetstream Series 200, and Jetstream Series 
3101 airplanes, all serial numbers, certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 32: Landing 
Gear.

(e) Reason

    This AD was prompted by mandatory continuing airworthiness 
information (MCAI) issued 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 cracking of the 
forward main landing gear yoke pintle resulting from corrosion pits 
which can cause stress corrosion cracking resulting in loss of 
control during take-off or landing. We are issuing this AD to revise 
the inspection procedure to detect smaller corrosion pits and cracks 
that could initiate stress corrosion cracking.

(f) Actions and Compliance

    Unless already done, do the following actions specified in 
paragraphs (f)(1) through (11) of this AD:
    (1) For all airplanes: Before or at the next inspection that 
would have been required by AD 2014-07-07 or within the next 30 days 
after the effective date of this AD, whichever occurs later, and 
repetitively thereafter at intervals not to exceed 12 months or 
1,200 main landing gear (MLG) flight cycles (FC), whichever occurs 
first, do a nondestructive testing (NDT) inspection of each MLG 
assembly cylinder attachment spigot housing following the 
Accomplishment Instructions in paragraph 2.B. Part A of British 
Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32-A-
JA851226, Revision 7, dated May 25, 2015.
    (2) For all airplanes: Within 300 landings after a heavy or 
abnormal landing or 3 months after a heavy or abnormal landing, 
whichever occurs first, do a NDT inspection of each MLG assembly 
cylinder attachment spigot housing following the accomplishment 
instructions in paragraph 2.B. Part A of British Aerospace Jetstream 
Series 3100 & 3200 Service Bulletin 32-A-JA851226, Revision 7, dated 
May 25, 2015.
    (3) For all airplanes: Within 3 months after accomplishment of 
the the latest NDT inspection required by paragraph (f)(1) of this 
AD or 300 MLG FC after accomplishment of the latest NDT inspection 
required by paragraph (f)(1) of this AD, whichever occurs first, and 
repetitively thereafter at intervals not to exceed 3 months or 300 
MLG FC, whichever occurs first, do a visual inspection of each MLG 
following the accomplishment instructions in paragraph 2.B. Part B 
of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 
32-A-JA851226, Revision 7, dated May 25, 2015. These inspections 
start over after every repetitive NDT inspection required by 
paragraph (f)(1)of this AD.
    (4) For all airplanes with a MLG incorporating a microswitch 
hole: Within the next 10,600 MLG FC since new and repetitively 
thereafter at intervals not to exceed 1,200 MLG flight cycles, do a 
NDT inspection of each MLG microswitch hole following the 
accomplishment instructions in paragraph 2.B. Part C of British 
Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32-A-
JA851226, Revision 7, dated May 25, 2015.
    (5) For all airplanes: If any discrepancy is found during any 
NDT inspection required in paragraphs (f)(1), (2), or (4) of this 
AD, before further flight, take all necessary corrective actions 
following the instructions in British Aerospace Jetstream Series 
3100 & 3200 Service Bulletin 32-A-JA851226, Revision 7, dated May 
25, 2015.
    (6) For all airplanes: If any discrepancy is found during any 
visual inspection required in paragraph (f)(3) of this AD, before 
further flight, take all necessary corrective actions following the 
instructions in British Aerospace Jetstream Series 3100 & 3200 
Service Bulletin 32-A-JA851226, Revision 7, dated May 25, 2015.
    (7) For all airplanes: Doing all necessary corrective actions 
required in paragraphs (f)(5) or (6) of this AD does not constitute 
terminating action for the inspections required by this AD.
    (8) For all airplanes: Modification of each MLG cylinder 
following BAE Systems (Operations) Ltd. Service Bulletin 32-JA880340 
original issue, dated January 6, 1989, constitutes terminating 
action for the inspections required by this AD for that MLG.
    (9) For all airplanes: The compliance times in paragraphs 
(f)(1), (2), (3), and (4) of this AD are presented in flight cycles 
(landings). If the total flight cycles have not been kept, multiply 
the total number of airplane hours time-in-service (TIS) by 0.75 to 
calculate the cycles. For the purposes of this AD:
    (i) 100 hours TIS x .75 = 75 cycles; and
    (ii) 1,000 hours TIS x .75 = 750 cycles.

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

    (1) This AD allows credit for the initial inspection required in 
paragraph (f)(1) of this AD if done before June 3, 2014 (the 
effective date retained from AD 2014-07-07) following British 
Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32-A-
JA851226, Revision 5, dated April 30, 2013.
    (2) This AD allows credit for the initial inspection required in 
paragraph (f)(4) of this AD if done before June 3, 2014 (the 
effective date retained from AD 2014-07-07) following APPH Ltd. 
Service Bulletin 32-40, at Initial Issue dated June 21, 1989.

(h) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, 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 Directorate, 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, a federal agency may not conduct or sponsor, and a person 
is not required to respond to, nor shall a person be subject to a 
penalty for failure to comply with a collection of information 
subject to the requirements of the Paperwork Reduction Act unless 
that collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response,

[[Page 10976]]

including the time for reviewing instructions, completing and 
reviewing the collection of information. All responses to this 
collection of information are mandatory. Comments concerning the 
accuracy of this burden and suggestions for reducing the burden 
should be directed to the FAA at: 800 Independence Ave. SW., 
Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(i) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 
2016-0224, dated November 9, 2016 for related information. You may 
examine the MCAI on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2017-0053. For service 
information related to this AD, contact BAE Systems (Operations) 
Ltd, Customer Information Department, Prestwick International 
Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; phone: +44 
1292 675207, fax: +44 1292 675704; email: 
RApublications@baesystems.com; Internet: http://www.jetstreamcentral.com. You may review copies of the 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.

    Issued in Kansas City, Missouri, on January 19, 2017.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-02771 Filed 2-16-17; 8:45 am]
 BILLING CODE 4910-13-P