Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 11315-11319 [2020-03932]

Download as PDF Federal Register / Vol. 85, No. 39 / Thursday, February 27, 2020 / Proposed Rules determinations which were previously made in connection with the issuance of the marketing order; and all said previous findings and determinations are hereby ratified and affirmed, except insofar as such findings and determinations may be in conflict with the findings and determinations set forth herein. 1. The Order, as amended, and as hereby proposed to be further amended, and all of the terms and conditions thereof, would tend to effectuate the declared policy of the Act; 2. The Order, as amended, and as hereby proposed to be further amended, regulates the handling of olives grown in California in the same manner as, and are applicable only to, persons in the respective classes of commercial and industrial activity specified in the Order; 3. The Order, as amended, and as hereby proposed to be further amended, is limited in application to the smallest regional production area which is practicable, consistent with carrying out the declared policy of the Act, and the issuance of several orders applicable to subdivisions of the production area would not effectively carry out the declared policy of the Act; 4. The Order, as amended, and as hereby proposed to be further amended, prescribe, insofar as practicable, such different terms applicable to different parts of the production area as are necessary to give due recognition to the differences in the production and marketing of olives produced in the production area; and 5. All handling of olives produced in the production area as defined in the Order is in the current of interstate or foreign commerce or directly burdens, obstructs, or affects such commerce. lotter on DSKBCFDHB2PROD with PROPOSALS Order Relative to Handling It is therefore ordered, that on and after the effective date hereof, all handling of olives grown in California shall be in conformity to, and in compliance with, the terms and conditions of the said order as hereby proposed to be amended as follows: The provisions of the proposed marketing order amending the Order contained in the proposed rule issued by the Administrator on November 1, 2019, and published in the Federal Register (84 FR 59736) on November 6, 2019, will be and are the terms and provisions of this order amending the Order and are set forth in full herein. formulate marketing agreements and marketing orders have been met. VerDate Sep<11>2014 16:50 Feb 26, 2020 Jkt 250001 PART 932—OLIVES GROWN IN CALIFORNIA 1. The authority citation for 7 CFR part 932 continues to read as follows: ■ ■ 11315 shall be required for adoption and, if the committee is increased by the addition of a public member, the number of affirmative votes required for adoption shall be increased by 1. Authority: 7 U.S.C. 601–674. [FR Doc. 2020–03893 Filed 2–26–20; 8:45 am] 2. Revise § 932.36 to read as follows: BILLING CODE 3410–02–P § 932.36 Procedure. Decisions of the committee shall be by majority vote of the members, including alternates acting as members, present and voting, and a quorum must be present: Provided, That decisions requiring a recommendation to the Secretary on matters pertaining to grade and size regulations shall require at least 10 affirmative votes, at least 5 of which must be from producer members and at least 5 of which must be from handler members and, if the committee is increased by the addition of a public member, at least 11 affirmative votes shall be required, at least 5 of which must be from producer members and at least 5 of which must be from handler members. A quorum shall consist of at least 10 members, including alternates acting as members, and, if the committee is increased by the addition of a public member, a quorum shall consist of at least 11 members, including alternates acting as members. Except in case of an emergency, a minimum of 5 days advance notice shall be given with respect to any meeting of the committee. In case of an emergency, to be determined within the discretion of the chairman of the committee, as much advance notice of a meeting as is practicable in the circumstances shall be given. The committee may vote by mail or telegram upon due notice to all members, but any proposition to be so voted upon first shall be explained accurately, fully, and identically by mail or telegram to all members. When voted on by such method, at least 14 affirmative votes, of which seven shall be producer member votes and seven shall be handler member votes, shall be required for adoption and, if the committee is increased by the addition of a public member, votes by mail or telegram shall require at least 15 affirmative votes, of which at least 7 shall be producer member votes and at least 7 shall be handler member votes. The committee may recommend for the Secretary’s approval changes in the number of affirmative votes required for adoption of any proposition voted upon by means of a mail or telegram ballot: Provided, That the number of affirmative votes required for adoption shall not be less than 10, and in any case an equal number of producer member and handler member votes PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–1123; Product Identifier 2017–SW–013–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening of comment period. AGENCY: The FAA is revising an earlier proposal for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB–BK 117 C–2 and Model MBB–BK 117 D–2 helicopters. This action revises the notice of proposed rulemaking (NPRM) by changing one of the required actions. The FAA is proposing this airworthiness directive (AD) to address the unsafe condition on these products. Since these actions impose an additional burden over that proposed in the NPRM, the FAA is reopening the comment period to allow the public the chance to comment on these proposed changes. DATES: The comment period for the NPRM published in the Federal Register on December 5, 2017 (82 FR 57390), is reopened. The FAA must receive comments on this SNPRM by April 27, 2020. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://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. SUMMARY: E:\FR\FM\27FEP1.SGM 27FEP1 11316 Federal Register / Vol. 85, No. 39 / Thursday, February 27, 2020 / Proposed Rules lotter on DSKBCFDHB2PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 1123; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the European Aviation Safety Agency (EASA) AD, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed rule, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone 972–641– 0000 or 800–232–0323; fax 972–641– 3775; or at https://www.airbus.com/ helicopters/services/technicalsupport.html. You may view 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 Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email matthew.fuller@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to participate in this rulemaking by submitting written comments, data, or views. The FAA also invites 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 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. The FAA will file in the docket all comments received, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, the FAA will consider all comments received on or before the closing date for comments. The FAA will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. The FAA may change VerDate Sep<11>2014 16:50 Feb 26, 2020 Jkt 250001 this proposal in light of the comments received. Discussion The FAA issued an NPRM to amend 14 CFR part 39 to remove AD 2017–02– 07, Amendment 39–18786 (82 FR 10267, February 10, 2017) (‘‘AD 2017– 02–07’’) and add a new AD. AD 2017– 02–07 applies to Airbus Helicopters Model MBB–BK 117 C–2 helicopters, serial numbers up to and including 9750, and Model MBB–BK 117 D–2 helicopters, serial numbers up to and including 20110, with a hydraulic module plate assembly part number B291M0003103 with a single locking attachment point installed. AD 2017– 02–07 requires a repetitive inspection and a one-time torque of the hydraulic module plate assembly attachment points (attachment points). The actions in AD 2017–02–07 are intended to prevent failure of an attachment point, loss of the hydraulic module plate, and subsequent loss of control of the helicopter. The NPRM published in the Federal Register on December 5, 2017 (82 FR 57390). The NPRM proposed to retain the initial inspection and torque requirements of AD 2017–02–07 and require replacing the single locking attachment mechanisms with double locking attachment mechanisms. The NPRM was prompted by EASA AD No. 2017–0047, dated March 13, 2017, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition on Airbus Helicopters Deutschland GmbH (formerly Eurocopter Deutschland GmbH) Model MBB–BK117 C–2, MBB–BK117 C–2e, MBB–BK117 D–2 and MBB–BK117 D– 2m helicopters. EASA advises that the hydraulic plate assembly on certain MBB–BK117 models has four attachment points on the fuselage secured by a single locking mechanism. According to EASA, a design reassessment revealed stiffness of the hydraulic plate may be insufficient to withstand the in-service loads in the event one of the four single locking attachment points fails. The EASA AD requires a repetitive inspection and onetime torque tightening of the attachment points until replacement of the single locking attachment hardware with double locking attachment hardware. Actions Since the NPRM Was Issued Since the NPRM was issued, Airbus Helicopters revised its service information by adding a requirement to reposition the aft grounding straps and inspect the clamping effect of the aft attachment points when the double PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 locking attachment hardware is installed. The revised service information also has an alternative clamp effect inspection for helicopters that have previously installed the double locking attachment hardware. These additional actions address the unsafe condition by ensuring the correct torque is applied and the bolts do not loosen. The FAA is proposing this SNPRM to include these additional actions. Further, the FAA has corrected an error in the NPRM proposing to apply a torque of 9 to 10 Nm to the left-hand and right-hand nuts of each attachment point. This torque adjustment is only necessary for each forward (not aft) attachment point. Lastly, the website address for Airbus Helicopters has also changed. This website address has been updated throughout this SNPRM. Comments The FAA gave the public the opportunity to comment on the original NPRM (82 FR 57390, December 5, 2017). The FAA received no comments on that NPRM or on the determination of the cost to the public. FAA’s Determination These helicopters have been approved by EASA and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the European Union, EASA has notified the FAA of the unsafe condition described in its AD. The FAA is proposing this SNPRM after evaluating all information provided by EASA and determining the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Certain changes described above expand the scope of the original NPRM. As a result, the FAA has determined that it is necessary to reopen the comment period to provide additional opportunity for the public to comment on this SNPRM. Related Service Information Under 1 CFR Part 51 The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. ASB MBB–BK117 C–2–29A–003 for Model MBB–BK 117 C–2 helicopters and ASB No. ASB MBB–BK117 D–2–29A–001 for Model MBB–BK 117 D–2 helicopters, both Revision 3 and dated December 19, 2017. Until the attachment points are modified with double locking attachment mechanisms, this service information specifies a repetitive visual inspection for condition and correct installation of the attachment points and replacing the affected parts if there is a crack. This service information also E:\FR\FM\27FEP1.SGM 27FEP1 Federal Register / Vol. 85, No. 39 / Thursday, February 27, 2020 / Proposed Rules specifies a tightening torque check of the forward attachment points after the initial inspection and replacing the affected parts if torque cannot be applied. This service information specifies procedures to replace the single locking attachment hardware with double locking attachment hardware. For certain helicopters with a hydraulic module plate assembly with the double locking attachment hardware installed, this revision of the service information contains procedures to inspect the clamping effect of the aft attachment points and torque tightening the screw joints (bolts). If a bolt can be turned while applying this torque, the service information specifies instructions to replace the split pin, washer, and self-locking castellated nut, check the bolt for wear and replace it if necessary, change the position of the aft grounding strap, check the electrical bonding, and apply PU-Lacquer to the grounding connection. 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. lotter on DSKBCFDHB2PROD with PROPOSALS Other Related Service Information The FAA also reviewed Airbus Helicopters ASB No. ASB MBB–BK117 C–2–29A–003 for Model MBB–BK 117 C–2 helicopters and ASB No. ASB MBB–BK117 D–2–29A–001 for Model MBB–BK 117 D–2 helicopters, both Revision 1 and dated October 14, 2016, and both Revision 2 and dated February 1, 2017. Revisions 1 and 2 of this service information contain the same visual inspection and torque tightening check procedures as Revision 3. Revision 2 of this service information adds the procedures to replace the single locking attachment hardware with double locking attachment hardware and contains the same forward locking attachment hardware replacement procedures as Revision 3. Proposed Requirements of the SNPRM For helicopters with a hydraulic module plate assembly with the single locking attachment hardware installed, this proposed AD would require, within 100 hours time-in-service (TIS), performing a visual inspection of each attachment point of the hydraulic module plate assembly for a crack and proper installation, and applying torque to the nuts of each forward attachment point. Within 300 hours TIS, this proposed AD would require replacing each single locking attachment point mechanism with a double locking attachment point mechanism. VerDate Sep<11>2014 16:50 Feb 26, 2020 Jkt 250001 For helicopters with a hydraulic module plate assembly with double locking attachment hardware installed in accordance with Airbus Helicopters ASB No. ASB MBB–BK117 C–2–29A– 003 or ASB No. ASB MBB–BK117 D–2– 29A–001, both Revision 2 and dated February 1, 2017, this proposed AD would require, within 300 hours TIS, inspecting the clamping effect of the aft joints and torque tightening the bolts. If a bolt can be turned while applying torque, this proposed AD would require removing the split pin and self-locking castellated nut from service, inspecting the bolt for wear and replacing it if necessary, repositioning the aft grounding strap to the opposite side of the attachment point, replacing the washer, installing a new self-locking castellated nut, inspecting the electrical bonding, installing a new split pin, and applying lacquer to the grounding connection. Differences Between This SNPRM and the EASA AD The EASA AD specifies performing the visual inspection of each attachment point at intervals not exceeding 400 flight hours. This proposed AD would not require a repetitive inspection. This proposed AD would require the replacement of each single locking attachment point mechanism with a double locking attachment point mechanism within 300 hours TIS instead, which would make subsequent inspections unnecessary. Since EASA has not revised or superseded its AD to incorporate Revision 3 of the service information, the EASA AD does not require inspecting the clamping effect of the aft joints, torque tightening the bolts, and corrective action if necessary for helicopters with a hydraulic module plate assembly with double locking attachment hardware installed in accordance with Airbus Helicopters ASB No. ASB MBB–BK117 C–2–29A– 003 or ASB No. ASB MBB–BK117 D–2– 29A–001, both Revision 2 and dated February 1, 2017. Costs of Compliance The FAA estimates that this proposed AD affects 167 helicopters of U.S. Registry. The FAA estimates that operators may incur the following costs in order to comply with this AD. The FAA estimates the cost of labor at $85 per work-hour. Visually inspecting the four attachment points would take about 0.75 work-hour for an estimated cost of $64 per helicopter and $10,688 for the U.S. fleet. Inspecting the torque of the four attachment points would take about 0.25 work-hour for an estimated cost of PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 11317 $21 per helicopter and $3,507 for the U.S. fleet. Replacing any of the attachment point parts would take a minimal amount of time and parts would cost about $48 per attachment point. Installing four double locking attachment point mechanisms would take a minimal amount of time and parts would cost about $400 per helicopter and $66,800 for the U.S. fleet. For certain double locking attachment hardware aft joints, inspecting the clamping effect and applying torque would take about 1 work-hour for an estimated cost of $85 per helicopter. If required, inspecting and replacing parts, repositioning the aft grounding strap, inspecting the electrical bonding, and applying lacquer to the grounding connection would take about 0.5 workhour and parts would cost about $15 for an estimated cost of $58 per helicopter. According to Airbus Helicopters’ service information, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. The FAA does not control warranty coverage by Airbus Helicopters. Accordingly, the FAA has included all costs in this cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. E:\FR\FM\27FEP1.SGM 27FEP1 11318 Federal Register / Vol. 85, No. 39 / Thursday, February 27, 2020 / Proposed Rules For the reasons discussed, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866, 2. Will not affect intrastate aviation in Alaska, and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by Reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2017–02–07, Amendment 39–18786 (82 FR 10267, February 10, 2017), and adding the following new AD: ■ Airbus Helicopters Deutschland GmbH: Docket No. FAA–2017–1123; Product Identifier 2017–SW–013–AD. lotter on DSKBCFDHB2PROD with PROPOSALS (a) Applicability This AD applies to Airbus Helicopters Deutschland GmbH Model MBB–BK 117 C– 2 helicopters, serial numbers up to and including 9750, and Airbus Helicopters Deutschland GmbH Model MBB–BK 117 D– 2 helicopters, serial numbers up to and including 20110, certificated in any category, with a hydraulic module plate assembly part number B291M0003103 with a single locking attachment point installed or with a double locking attachment point installed before the effective date of this AD in accordance with Airbus Helicopters Alert Service Bulletin (ASB) No. ASB MBB–BK117 C–2–29A–003 (ASB MBB–BK117 C–2–29A–003 Rev 2) or ASB No. ASB MBB–BK117 D–2–29A–001 (ASB MBB–BK117 D–2–29A–001 Rev 2), both Revision 2 and dated February 1, 2017, as applicable to your model helicopter. (b) Unsafe Condition This AD defines the unsafe condition as failure of a hydraulic module plate assembly attachment point (attachment point). This condition could result in loss of the hydraulic module plate and subsequent loss of control of the helicopter. (c) Affected ADs This AD replaces 2017–02–07, Amendment 39–18786 (82 FR 10267, February 10, 2017). VerDate Sep<11>2014 16:50 Feb 26, 2020 Jkt 250001 (d) Comments Due Date The FAA must receive comments by April 27, 2020. (e) 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. (f) Required Actions Comply with either paragraphs (f)(1) and (2) of this AD, or paragraph (f)(3) of this AD, as applicable to your helicopter. (1) For helicopters with a hydraulic module plate assembly with a single locking attachment hardware installed, within 100 hours time-in-service (TIS): (i) Visually inspect the split pins, castellated nuts, plugs, nuts, and hexagon bolts of each attachment point for a crack and for proper installation by following the Accomplishment Instructions, paragraphs 3.B.1.3.a. through 3.B.1.3.d., of Airbus Helicopters ASB No. ASB MBB–BK117 C–2– 29A–003 (ASB MBB–BK117 C–2–29A–003 Rev 3) or Airbus Helicopters ASB No. ASB MBB–BK117 D–2–29A–001 (ASB MBB– BK117 D–2–29A–001 Rev 3), both Revision 3 and dated December 19, 2017, as applicable to your model helicopter. Replace any part that has a crack before further flight. If the split pins, castellated nuts, or hexagon bolts are not as depicted in Figures 1 and 2 of ASB MBB–BK117 C–2–29A–003 Rev 3 or ASB MBB–BK117 D–2–29A–001 Rev 3, before further flight, properly install them. (ii) Apply a torque of 9 to 10 Nm to the left-hand (LH) and right-hand (RH) nuts of each forward attachment point. If a torque of 9 to 10 Nm cannot be applied, replace the affected nut before further flight. (2) For helicopters with a hydraulic module plate assembly with a single locking attachment hardware installed, within 300 hours TIS: (i) Replace each forward single locking attachment hardware with double locking attachment hardware by following the Accomplishment Instructions, paragraphs 3.B.3.3. through 3.B.3.6. on page 11 of ASB MBB–BK117 C–2–29A–003 Rev 3 or ASB MBB–BK117 D–2–29A–001 Rev 3, as applicable to your model helicopter, except you are not required to discard old parts. (ii) Replace each aft single locking attachment hardware with double locking attachment hardware and reposition the LH and RH aft grounding straps by following the Accomplishment Instructions, paragraphs 3.B.3.1. through 3.B.3.7. on page 13 of ASB MBB–BK117 C–2–29A–003 Rev 3 or ASB MBB–BK117 D–2–29A–001 Rev 3, as applicable to your model helicopter, except you are not required to discard old parts. (3) If you have replaced the attachment hardware with double locking attachment hardware before the effective date of this AD in accordance with ASB MBB–BK117 C–2– 29A–003 Rev 2 or ASB MBB–BK117 D–2– 29A–001 Rev 2, as applicable to your model helicopter: Within 300 hours TIS, inspect the clamping effect of the LH and RH aft screw joints (bolts) of the hydraulic module plate by following the Accomplishment Instructions, paragraph 3.B.5., of ASB MBB– PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 BK117 C–2–29A–003 Rev 3 or ASB MBB– BK117 D–2–29A–001 Rev 3, as applicable to your model helicopter, except you are not required to discard old parts. Note 1 to paragraph (f)(3) of this AD: Airbus Helicopters refers to bolts as ‘‘screw joints.’’ (g) Credit for Previous Actions Actions accomplished before the effective date of this AD in accordance with the procedures specified in the following are considered acceptable for compliance with the corresponding actions in paragraph (f)(1) of this AD: (1) AD 2017–02–07, Amendment 39–18786 (82 FR 10267, February 10, 2017). (2) Airbus Helicopters ASB No. ASB MBB– BK117 C–2–29A–003, Revision 1, dated October 14, 2016. (3) Airbus Helicopters ASB No. ASB MBB– BK117 C–2–29A–003, Revision 2, dated February 1, 2017. (4) Airbus Helicopters ASB No. ASB MBB– BK117 D–2–29A–001, Revision 1, dated October 14, 2016. (5) Airbus Helicopters ASB No. ASB MBB– BK117 D–2–29A–001, Revision 2, dated February 1, 2017. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email 9-ASW-FTWAMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests 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. (i) Additional Information (1) Airbus Helicopters ASB No. ASB MBB– BK117 C–2–29A–003 and ASB No. ASB MBB–BK117 D–2–29A–001, both Revision 1 and dated October 14, 2016, and both Revision 2 and dated February 1, 2017, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone 972–641–0000 or 800–232–0323; fax 972–641–3775; or at https://www.airbus.com/helicopters/services/ technical-support.html. You may view a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2017–0047, dated March 13, 2017. You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA–2017–1123. E:\FR\FM\27FEP1.SGM 27FEP1 Federal Register / Vol. 85, No. 39 / Thursday, February 27, 2020 / Proposed Rules (j) Subject Joint Aircraft Service Component (JASC) Code: 2900, Hydraulic Power System. Issued in Fort Worth, Texas, on February 14, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–03932 Filed 2–26–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0103; Product Identifier 2019–NM–149–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2012–21–08, which applies to certain The Boeing Company Model 737–600, –700, –700C, –800, and –900 series airplanes. AD 2012–21–08 requires inspecting for part numbers of the operational program software (OPS) of the flight control computers (FCCs) and installing and testing an updated version of the FCC OPS. Since the FAA issued AD 2012–21–08, the FAA has determined that there is a new unsafe condition which must be addressed by an updated version of the FCC OPS. This proposed AD would retain the requirement to inspect for part numbers of the OPS of the FCCs, and add a new requirement to update the version of the FCC OPS if necessary. This proposed AD would also expand the applicability to include The Boeing Company Model 737–900ER series airplanes. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by April 13, 2020. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room lotter on DSKBCFDHB2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:50 Feb 26, 2020 Jkt 250001 W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https:// www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0103. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0103; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: David Sumner, Aerospace Engineer, Systems and Equipment Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3538; email: david.sumner@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2020–0103; Product Identifier 2019–NM–149–AD’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date and may amend this NPRM because of those comments. The FAA will post all comments, without change, to https:// www.regulations.gov, including any personal information you provide. The PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 11319 FAA will also post a report summarizing each substantive verbal contact the agency receives about this proposed AD. Discussion The FAA issued AD 2012–21–08, Amendment 39–17224 (77 FR 64711, October 23, 2012) (‘‘AD 2012–21–08’’), for certain The Boeing Company Model 737–600, –700, –700C, –800, and –900 series airplanes. AD 2012–21–08 requires inspecting for part numbers of the OPS of the FCCs and installing and testing an updated version of the FCC OPS. AD 2012–21–08 resulted from reports of undetected erroneous output from a single radio altimeter channel, which resulted in premature autothrottle retard during approach. The FAA issued AD 2012–21–08 to address this condition, which, if not detected and corrected, could result in the loss of automatic speed control, and consequent loss of control of the airplane. Actions Since AD 2012–21–08 Was Issued Since the FAA issued AD 2012–21– 08, the FAA has received reports that during autopilot coupled Instrument Landing System (ILS) approaches, the airplane did not capture or track the glideslope correctly. This caused airplanes to continue descending below the glideslope without any fault indication from the autopilot system. The problems were reported with the autopilot engaged while attempting to capture the glideslope from above, with a high descent rate greater than 2,000 feet per minute and late arming of approach mode. The high descent rate is maintained by the autopilot and can result in the airplane descending below the glideslope beam, which requires the flight crew to correct the problem manually. Boeing has developed an upgrade to the FCC OPS for certain affected airplanes equipped with Rockwell Collins FCCs that corrects the glideslope capture problem. The FAA is proposing this AD to address this condition, which can result in controlled flight into terrain on airplanes that do not have the upgraded FCC OPS installed. Related Service Information Under 1 CFR Part 51 The FAA reviewed Boeing Alert Requirements Bulletin 737–22A1322 RB, dated November 21, 2018. The service information describes procedures for installing and testing an updated version of the FCC OPS. This proposed AD would also require Boeing Alert Service Bulletin 737– E:\FR\FM\27FEP1.SGM 27FEP1

Agencies

[Federal Register Volume 85, Number 39 (Thursday, February 27, 2020)]
[Proposed Rules]
[Pages 11315-11319]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-03932]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1123; Product Identifier 2017-SW-013-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening 
of comment period.

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

SUMMARY: The FAA is revising an earlier proposal for Airbus Helicopters 
Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 and Model 
MBB-BK 117 D-2 helicopters. This action revises the notice of proposed 
rulemaking (NPRM) by changing one of the required actions. The FAA is 
proposing this airworthiness directive (AD) to address the unsafe 
condition on these products. Since these actions impose an additional 
burden over that proposed in the NPRM, the FAA is reopening the comment 
period to allow the public the chance to comment on these proposed 
changes.

DATES: The comment period for the NPRM published in the Federal 
Register on December 5, 2017 (82 FR 57390), is reopened. The FAA must 
receive comments on this SNPRM by April 27, 2020.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://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.

[[Page 11316]]

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1123; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this proposed AD, the European Aviation Safety Agency (EASA) AD, any 
comments received, and other information. The street address for Docket 
Operations is listed above. Comments will be available in the AD docket 
shortly after receipt.
    For service information identified in this proposed rule, contact 
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; 
telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. You may 
view 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 Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; 
email [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to participate in this rulemaking by submitting 
written comments, data, or views. The FAA also invites 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 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.
    The FAA will file in the docket all comments received, as well as a 
report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, 
the FAA will consider all comments received on or before the closing 
date for comments. The FAA will consider comments filed after the 
comment period has closed if it is possible to do so without incurring 
expense or delay. The FAA may change this proposal in light of the 
comments received.

Discussion

    The FAA issued an NPRM to amend 14 CFR part 39 to remove AD 2017-
02-07, Amendment 39-18786 (82 FR 10267, February 10, 2017) (``AD 2017-
02-07'') and add a new AD. AD 2017-02-07 applies to Airbus Helicopters 
Model MBB-BK 117 C-2 helicopters, serial numbers up to and including 
9750, and Model MBB-BK 117 D-2 helicopters, serial numbers up to and 
including 20110, with a hydraulic module plate assembly part number 
B291M0003103 with a single locking attachment point installed. AD 2017-
02-07 requires a repetitive inspection and a one-time torque of the 
hydraulic module plate assembly attachment points (attachment points). 
The actions in AD 2017-02-07 are intended to prevent failure of an 
attachment point, loss of the hydraulic module plate, and subsequent 
loss of control of the helicopter.
    The NPRM published in the Federal Register on December 5, 2017 (82 
FR 57390). The NPRM proposed to retain the initial inspection and 
torque requirements of AD 2017-02-07 and require replacing the single 
locking attachment mechanisms with double locking attachment 
mechanisms. The NPRM was prompted by EASA AD No. 2017-0047, dated March 
13, 2017, issued by EASA, which is the Technical Agent for the Member 
States of the European Union, to correct an unsafe condition on Airbus 
Helicopters Deutschland GmbH (formerly Eurocopter Deutschland GmbH) 
Model MBB-BK117 C-2, MBB-BK117 C-2e, MBB-BK117 D-2 and MBB-BK117 D-2m 
helicopters. EASA advises that the hydraulic plate assembly on certain 
MBB-BK117 models has four attachment points on the fuselage secured by 
a single locking mechanism. According to EASA, a design reassessment 
revealed stiffness of the hydraulic plate may be insufficient to 
withstand the in-service loads in the event one of the four single 
locking attachment points fails. The EASA AD requires a repetitive 
inspection and one-time torque tightening of the attachment points 
until replacement of the single locking attachment hardware with double 
locking attachment hardware.

Actions Since the NPRM Was Issued

    Since the NPRM was issued, Airbus Helicopters revised its service 
information by adding a requirement to reposition the aft grounding 
straps and inspect the clamping effect of the aft attachment points 
when the double locking attachment hardware is installed. The revised 
service information also has an alternative clamp effect inspection for 
helicopters that have previously installed the double locking 
attachment hardware. These additional actions address the unsafe 
condition by ensuring the correct torque is applied and the bolts do 
not loosen. The FAA is proposing this SNPRM to include these additional 
actions.
    Further, the FAA has corrected an error in the NPRM proposing to 
apply a torque of 9 to 10 Nm to the left-hand and right-hand nuts of 
each attachment point. This torque adjustment is only necessary for 
each forward (not aft) attachment point.
    Lastly, the website address for Airbus Helicopters has also 
changed. This website address has been updated throughout this SNPRM.

Comments

    The FAA gave the public the opportunity to comment on the original 
NPRM (82 FR 57390, December 5, 2017). The FAA received no comments on 
that NPRM or on the determination of the cost to the public.

FAA's Determination

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA of the 
unsafe condition described in its AD. The FAA is proposing this SNPRM 
after evaluating all information provided by EASA and determining the 
unsafe condition exists and is likely to exist or develop on other 
helicopters of these same type designs. Certain changes described above 
expand the scope of the original NPRM. As a result, the FAA has 
determined that it is necessary to reopen the comment period to provide 
additional opportunity for the public to comment on this SNPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) 
No. ASB MBB-BK117 C-2-29A-003 for Model MBB-BK 117 C-2 helicopters and 
ASB No. ASB MBB-BK117 D-2-29A-001 for Model MBB-BK 117 D-2 helicopters, 
both Revision 3 and dated December 19, 2017. Until the attachment 
points are modified with double locking attachment mechanisms, this 
service information specifies a repetitive visual inspection for 
condition and correct installation of the attachment points and 
replacing the affected parts if there is a crack. This service 
information also

[[Page 11317]]

specifies a tightening torque check of the forward attachment points 
after the initial inspection and replacing the affected parts if torque 
cannot be applied. This service information specifies procedures to 
replace the single locking attachment hardware with double locking 
attachment hardware.
    For certain helicopters with a hydraulic module plate assembly with 
the double locking attachment hardware installed, this revision of the 
service information contains procedures to inspect the clamping effect 
of the aft attachment points and torque tightening the screw joints 
(bolts). If a bolt can be turned while applying this torque, the 
service information specifies instructions to replace the split pin, 
washer, and self-locking castellated nut, check the bolt for wear and 
replace it if necessary, change the position of the aft grounding 
strap, check the electrical bonding, and apply PU-Lacquer to the 
grounding connection.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Other Related Service Information

    The FAA also reviewed Airbus Helicopters ASB No. ASB MBB-BK117 C-2-
29A-003 for Model MBB-BK 117 C-2 helicopters and ASB No. ASB MBB-BK117 
D-2-29A-001 for Model MBB-BK 117 D-2 helicopters, both Revision 1 and 
dated October 14, 2016, and both Revision 2 and dated February 1, 2017. 
Revisions 1 and 2 of this service information contain the same visual 
inspection and torque tightening check procedures as Revision 3. 
Revision 2 of this service information adds the procedures to replace 
the single locking attachment hardware with double locking attachment 
hardware and contains the same forward locking attachment hardware 
replacement procedures as Revision 3.

Proposed Requirements of the SNPRM

    For helicopters with a hydraulic module plate assembly with the 
single locking attachment hardware installed, this proposed AD would 
require, within 100 hours time-in-service (TIS), performing a visual 
inspection of each attachment point of the hydraulic module plate 
assembly for a crack and proper installation, and applying torque to 
the nuts of each forward attachment point. Within 300 hours TIS, this 
proposed AD would require replacing each single locking attachment 
point mechanism with a double locking attachment point mechanism.
    For helicopters with a hydraulic module plate assembly with double 
locking attachment hardware installed in accordance with Airbus 
Helicopters ASB No. ASB MBB-BK117 C-2-29A-003 or ASB No. ASB MBB-BK117 
D-2-29A-001, both Revision 2 and dated February 1, 2017, this proposed 
AD would require, within 300 hours TIS, inspecting the clamping effect 
of the aft joints and torque tightening the bolts. If a bolt can be 
turned while applying torque, this proposed AD would require removing 
the split pin and self-locking castellated nut from service, inspecting 
the bolt for wear and replacing it if necessary, repositioning the aft 
grounding strap to the opposite side of the attachment point, replacing 
the washer, installing a new self-locking castellated nut, inspecting 
the electrical bonding, installing a new split pin, and applying 
lacquer to the grounding connection.

Differences Between This SNPRM and the EASA AD

    The EASA AD specifies performing the visual inspection of each 
attachment point at intervals not exceeding 400 flight hours. This 
proposed AD would not require a repetitive inspection. This proposed AD 
would require the replacement of each single locking attachment point 
mechanism with a double locking attachment point mechanism within 300 
hours TIS instead, which would make subsequent inspections unnecessary. 
Since EASA has not revised or superseded its AD to incorporate Revision 
3 of the service information, the EASA AD does not require inspecting 
the clamping effect of the aft joints, torque tightening the bolts, and 
corrective action if necessary for helicopters with a hydraulic module 
plate assembly with double locking attachment hardware installed in 
accordance with Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003 or 
ASB No. ASB MBB-BK117 D-2-29A-001, both Revision 2 and dated February 
1, 2017.

Costs of Compliance

    The FAA estimates that this proposed AD affects 167 helicopters of 
U.S. Registry. The FAA estimates that operators may incur the following 
costs in order to comply with this AD. The FAA estimates the cost of 
labor at $85 per work-hour.
    Visually inspecting the four attachment points would take about 
0.75 work-hour for an estimated cost of $64 per helicopter and $10,688 
for the U.S. fleet. Inspecting the torque of the four attachment points 
would take about 0.25 work-hour for an estimated cost of $21 per 
helicopter and $3,507 for the U.S. fleet. Replacing any of the 
attachment point parts would take a minimal amount of time and parts 
would cost about $48 per attachment point. Installing four double 
locking attachment point mechanisms would take a minimal amount of time 
and parts would cost about $400 per helicopter and $66,800 for the U.S. 
fleet.
    For certain double locking attachment hardware aft joints, 
inspecting the clamping effect and applying torque would take about 1 
work-hour for an estimated cost of $85 per helicopter. If required, 
inspecting and replacing parts, repositioning the aft grounding strap, 
inspecting the electrical bonding, and applying lacquer to the 
grounding connection would take about 0.5 work-hour and parts would 
cost about $15 for an estimated cost of $58 per helicopter.
    According to Airbus Helicopters' service information, some of the 
costs of this proposed AD may be covered under warranty, thereby 
reducing the cost impact on affected individuals. The FAA does not 
control warranty coverage by Airbus Helicopters. Accordingly, the FAA 
has included all costs in this cost estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.

[[Page 11318]]

    For the reasons discussed, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866,
    2. Will not affect intrastate aviation in Alaska, and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2017-02-07, Amendment 39-18786 (82 FR 10267, February 10, 2017), and 
adding the following new AD:

Airbus Helicopters Deutschland GmbH: Docket No. FAA-2017-1123; 
Product Identifier 2017-SW-013-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Deutschland GmbH Model 
MBB-BK 117 C-2 helicopters, serial numbers up to and including 9750, 
and Airbus Helicopters Deutschland GmbH Model MBB-BK 117 D-2 
helicopters, serial numbers up to and including 20110, certificated 
in any category, with a hydraulic module plate assembly part number 
B291M0003103 with a single locking attachment point installed or 
with a double locking attachment point installed before the 
effective date of this AD in accordance with Airbus Helicopters 
Alert Service Bulletin (ASB) No. ASB MBB-BK117 C-2-29A-003 (ASB MBB-
BK117 C-2-29A-003 Rev 2) or ASB No. ASB MBB-BK117 D-2-29A-001 (ASB 
MBB-BK117 D-2-29A-001 Rev 2), both Revision 2 and dated February 1, 
2017, as applicable to your model helicopter.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a hydraulic 
module plate assembly attachment point (attachment point). This 
condition could result in loss of the hydraulic module plate and 
subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD replaces 2017-02-07, Amendment 39-18786 (82 FR 10267, 
February 10, 2017).

(d) Comments Due Date

    The FAA must receive comments by April 27, 2020.

(e) 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.

(f) Required Actions

    Comply with either paragraphs (f)(1) and (2) of this AD, or 
paragraph (f)(3) of this AD, as applicable to your helicopter.
    (1) For helicopters with a hydraulic module plate assembly with 
a single locking attachment hardware installed, within 100 hours 
time-in-service (TIS):
    (i) Visually inspect the split pins, castellated nuts, plugs, 
nuts, and hexagon bolts of each attachment point for a crack and for 
proper installation by following the Accomplishment Instructions, 
paragraphs 3.B.1.3.a. through 3.B.1.3.d., of Airbus Helicopters ASB 
No. ASB MBB-BK117 C-2-29A-003 (ASB MBB-BK117 C-2-29A-003 Rev 3) or 
Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001 (ASB MBB-BK117 
D-2-29A-001 Rev 3), both Revision 3 and dated December 19, 2017, as 
applicable to your model helicopter. Replace any part that has a 
crack before further flight. If the split pins, castellated nuts, or 
hexagon bolts are not as depicted in Figures 1 and 2 of ASB MBB-
BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, before 
further flight, properly install them.
    (ii) Apply a torque of 9 to 10 Nm to the left-hand (LH) and 
right-hand (RH) nuts of each forward attachment point. If a torque 
of 9 to 10 Nm cannot be applied, replace the affected nut before 
further flight.
    (2) For helicopters with a hydraulic module plate assembly with 
a single locking attachment hardware installed, within 300 hours 
TIS:
    (i) Replace each forward single locking attachment hardware with 
double locking attachment hardware by following the Accomplishment 
Instructions, paragraphs 3.B.3.3. through 3.B.3.6. on page 11 of ASB 
MBB-BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as 
applicable to your model helicopter, except you are not required to 
discard old parts.
    (ii) Replace each aft single locking attachment hardware with 
double locking attachment hardware and reposition the LH and RH aft 
grounding straps by following the Accomplishment Instructions, 
paragraphs 3.B.3.1. through 3.B.3.7. on page 13 of ASB MBB-BK117 C-
2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as applicable to 
your model helicopter, except you are not required to discard old 
parts.
    (3) If you have replaced the attachment hardware with double 
locking attachment hardware before the effective date of this AD in 
accordance with ASB MBB-BK117 C-2-29A-003 Rev 2 or ASB MBB-BK117 D-
2-29A-001 Rev 2, as applicable to your model helicopter: Within 300 
hours TIS, inspect the clamping effect of the LH and RH aft screw 
joints (bolts) of the hydraulic module plate by following the 
Accomplishment Instructions, paragraph 3.B.5., of ASB MBB-BK117 C-2-
29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as applicable to 
your model helicopter, except you are not required to discard old 
parts.

    Note 1 to paragraph (f)(3) of this AD: Airbus Helicopters refers 
to bolts as ``screw joints.''

(g) Credit for Previous Actions

    Actions accomplished before the effective date of this AD in 
accordance with the procedures specified in the following are 
considered acceptable for compliance with the corresponding actions 
in paragraph (f)(1) of this AD:
    (1) AD 2017-02-07, Amendment 39-18786 (82 FR 10267, February 10, 
2017).
    (2) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003, 
Revision 1, dated October 14, 2016.
    (3) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003, 
Revision 2, dated February 1, 2017.
    (4) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001, 
Revision 1, dated October 14, 2016.
    (5) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001, 
Revision 2, dated February 1, 2017.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards 
Branch, FAA, may approve AMOCs for this AD. Send your proposal to: 
Matt Fuller, Senior Aviation Safety Engineer, Safety Management 
Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., 
Fort Worth, TX 76177; telephone 817-222-5110; email [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, the FAA suggests 
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.

(i) Additional Information

    (1) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003 and ASB 
No. ASB MBB-BK117 D-2-29A-001, both Revision 1 and dated October 14, 
2016, and both Revision 2 and dated February 1, 2017, which are not 
incorporated by reference, contain additional information about the 
subject of this AD. For service information identified in this AD, 
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 
75052; telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or 
at https://www.airbus.com/helicopters/services/technical-support.html. You may view a copy of the service information at the 
FAA, Office of the Regional Counsel, Southwest Region, 10101 
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2017-0047, dated March 13, 2017. You may 
view the EASA AD on the internet at https://www.regulations.gov in 
Docket No. FAA-2017-1123.

[[Page 11319]]

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 2900, Hydraulic 
Power System.

    Issued in Fort Worth, Texas, on February 14, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-03932 Filed 2-26-20; 8:45 am]
BILLING CODE 4910-13-P