Accepted Means of Compliance; Airworthiness Standards: Normal Category Airplanes, 21850-21855 [2018-09990]

Download as PDF 21850 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Rules and Regulations defined as within the past two years from the date of the letter requesting the waiver; and the amount of the request. § 3419.5 [Amended] 8. Amend § 3419.5 by removing the word ‘‘formula’’ and adding, in its place, the word ‘‘capacity’’. ■ 9. Revise § 3419.6 to read as follows: ■ § 3419.6 Use of matching funds. The required matching funds for the capacity programs must be used by an eligible institution for the same purpose as Federal award dollars: Agricultural research and extension activities that have been approved in the plan of work required under sections 1445(c) and 1444(d) of the National Agricultural Research, Extension, and Teaching Policy Act of 1977, section 7 of the Hatch Act of 1887, and section 4 of the Smith-Lever Act. For all programs, tuition dollars and student fees may not be used as matching funds. ■ 10. Redesignate § 3419.7 as § 3419.8 and revise newly redesignated § 3419.8 to read as follows: § 3419.8 Redistribution of funds. Unmatched research and extension funds will be reapportioned in accordance with the research and extension statutory distribution formulas applicable to the 1890 and 1862 land-grant institutions in insular areas, respectively. Any redistribution of funds must be subject to the same matching requirement under § 3419.2. ■ 11. Add a new § 3419.7 to read as follows: § 3419.7 Reporting of matching funds. Institutions will report all capacity matching funds expended annually using Standard Form (SF) 425, in accordance with 7 CFR 3430.56(a). Done at Washington, DC, this 7th day of May 2018. Meryl Broussard, Associate Director for Programs, National Institute of Food and Agriculture. BILLING CODE 3410–22–P DEPARTMENT OF TRANSPORTATION sradovich on DSK3GMQ082PROD with RULES 14 CFR Part 23 [Notice No. 23–18–01–NOA] Accepted Means of Compliance; Airworthiness Standards: Normal Category Airplanes Federal Aviation Administration, DOT. AGENCY: VerDate Sep<11>2014 22:27 May 10, 2018 Jkt 244001 This document announces the availability of 63 Means of Compliance (MOC) based on 30 published ASTM International (ASTM) consensus standards developed by ASTM Committee F44 on General Aviation Aircraft. A total of 46 of these accepted MOCs consist of ASTM consensus standards as published, with the remaining 17 MOCs comprised of a combination of ASTM standards and FAA changes. The Administrator finds these MOCs to be an acceptable means, but not the only means, of showing compliance to the applicable regulations in part 23, amendment 23–64, for normal category airplanes. The Administrator further finds that these accepted means of complying with part 23, amendment 23–64, provide at least the same level of safety as the corresponding requirements in part 23, amendment 23–63. DATES: Comments must be received on or before July 10, 2018. ADDRESSES: Mail comments to: Federal Aviation Administration, Policy and Innovation Division, Small Airplane Standards Branch, AIR–690, Attention: Steve Thompson, 901 Locust Street, Room 301, Kansas City, Missouri 64106. Comments may also be emailed to: steven.thompson@faa.gov. Specify the MOC, and if applicable, the standard being addressed by designation and title. Mark all comments: Part 23 MOC Comments. FOR FURTHER INFORMATION CONTACT: Steve Thompson, Federal Aviation Administration, Policy and Innovation Division, Small Airplane Standards Branch, AIR–690, 901 Locust Street, Room 301, Kansas City, Missouri 64106; telephone (816) 329–4126; facsimile: (816) 329–4090; email: steven.thompson@faa.gov. SUPPLEMENTARY INFORMATION: SUMMARY: Comments Invited [FR Doc. 2018–10015 Filed 5–10–18; 8:45 am] Federal Aviation Administration Notification of availability; request for comments. ACTION: Interested persons are invited to submit written comments, data, or views. Communications should identify the MOC and consensus standard number, where applicable, and be submitted to the address previously specified in the ADDRESSES section of this NOA. The most helpful comments reference a specific portion of the accepted MOC(s) or standard(s), explain the reason for any recommended change, and include supporting data. The FAA may forward communications regarding the consensus standards to ASTM Committee F44 for consideration. The MOC or standard may be revised PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 based on received comments. The FAA will consider all comments received during the recurring review of the MOC and consensus standard and will participate in the consensus standard revision process. Background Under the provisions of the National Technology Transfer and Advancement Act of 1995 1 and Office of Management and Budget (OMB) Circular A–119, ‘‘Federal Participation in the Development and Use of Voluntary Consensus Standards and in Conformity Assessment Activities,’’ effective January 27, 2016, the FAA participates in the development of consensus standards and uses consensus standards as a means of carrying out its policy objectives where appropriate. Consistent with the Small Airplane Revitalization Act of 2013,2 the FAA has been working with industry and other stakeholders through ASTM to develop consensus standards for use as a MOC in certificating small airplanes under part 23. In promulgating part 23, amendment 23–64, the FAA explained that if it determined such consensus standards were acceptable MOC to part 23, it would publish a notice of availability of those consensus standards in the Federal Register. Pursuant to FAA Advisory Circular 23.2010–1, section 3.1.1, this document serves as a formal acceptance by the Administrator, of MOCs based on consensus standards developed by ASTM. The MOCs accepted by this document are one means, but not the only means of complying with part 23 regulatory requirements. The FAA has reviewed the consensus standards referenced in this NOA as the basis for MOCs to the regulatory requirements of part 23, amendment 23– 64. In some cases, the Administrator finds sections of ASTM Standard F3264–17, ‘‘Standard Specification for Normal Category Aeroplanes Certification,’’ without changes, are accepted as means of complying with the airworthiness requirements of part 23, without degrading safety, and within the scope and applicability of the consensus standards. In other cases, the MOCs, while based on ASTM consensus standards, include additional FAA provisions necessary to comply with the airworthiness requirements of part 23, amendment 23–64. Part 23, amendment 23–64, established airworthiness requirements based on the level of safety of 1 Ref Public Law 104–113 as amended by Public Law 107–107. 2 Ref Public Law 113–53. E:\FR\FM\11MYR1.SGM 11MYR1 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Rules and Regulations amendment 23–63 regulations, except for areas addressing loss of control and icing where the safety level was increased.3 Achieving this level of safety through compliance with amendment 23–64—for a given certification project—may require use of additional MOCs beyond those accepted by this document, depending on the details of the specific design. For example, an applicant’s design may include features that are customary, but not addressed in the MOCs accepted by this document. Designs may also include features that are innovative and not type certificated previously. In either case, a supplemental MOC beyond those accepted in this document would be required. For example, the MOCs accepted by this document do not contain provisions addressing powered- trim system runaways. Therefore, in order to maintain the level of safety of amendment 23–63 regulations, applicants proposing use of these MOCs for an airplane with a powered-trim system would need to supplement the accepted MOC(s) with additional means for § 23.2300 to demonstrate safe controllability after a probable trim system runaway. To do this, applicants could use the provisions of § 23.677(d), amendment 23–49, or other MOC(s) accepted under § 23.2010. Further information on supplemental MOCs is provided in a part 23 means of compliance summary table and in the Small Airplanes Issues List, which are available on the Small Airplanes— Regulations, Policies & Guidance website.4 21851 Means of Compliance Accepted in This Document The following is a list of sections from part 23, amendment 23–64, followed by their corresponding MOC accepted by this document: 23.1457: ASTM F3264–17, section 9.12 23.1459: ASTM F3264–17, section 9.13 23.1529: ASTM F3264–17, section 10.6 Subpart B—Flight 23.2100: ASTM F3264–17, section 5.1 23.2105: ASTM F3264–17, section 5.2 23.2110: ASTM F3264–17, section 5.3 23.2115: ASTM F3264–17, section 5.4 23.2120: ASTM F3264–17, section 5.5 23.2125: ASTM F3264–17, section 5.6 23.2130: ASTM F3264–17, section 5.7 23.2135: ASTM F3264–17, section 5.8, combined with the changes in the following table: Replace: With: ASTM F3173/F3173M–17, Sections 4.9.1.1 and 4.9.1.2. FAA 4.9.1.1 and 4.9.1.2: 4.9.1.1: ‘‘For a level 1 or 2 airplane, or level 3 or 4 airplane of 6,000 pounds or less maximum weight, 5 seconds from initiation of roll and’’ 4.9.1.2: ‘‘For a level 3 or 4 airplane of over 6,000 pounds maximum weight, (W+500)/1300 seconds, but not more than 10 seconds, where W is the weight in pounds.’’ FAA 4.9.3.1 and 4.9.3.2: 4.9.3.1: ‘‘For a level 1 or 2 airplane, or level 3 or 4 airplane of 6,000 pounds or less maximum weight, 4 seconds from initiation of roll and’’ 4.9.3.2: ‘‘For a level 3 or 4 airplane of over 6,000 pounds maximum weight, (W+2,800)/2,200 seconds, but not more than 7 seconds, where W is the weight in pounds.’’ ASTM F3173/F3173M–17, Sections 4.9.3.1 and 4.9.3.2. 23.2140: ASTM F3264–17, section 5.9 23.2145: ASTM F3264–17, section 5.10 23.2150: ASTM F3264–17, section 5.11 23.2155: ASTM F3264–17, section 5.12 23.2160: ASTM F3264–17, section 5.13 23.2165: ASTM F3264–17, section 5.14 Subpart C—Structures 23.2200: ASTM F3264–17, Section 6.1, combined with the changes in the following table: Replace: With: ASTM F3116/F3116M–15, Section 5.1.3.1(1). FAA 5.1.3.1(1): ‘‘VS is a 1g computed stalling speed with flaps retracted (normally based on the maximum airplane normal force coefficient, CNA) at the design maximum takeoff weight.’’ 23.2210: ASTM F3264–17, section 6.3 23.2215: ASTM F3264–17, section 6.4, combined with the changes in the following table: Replace: With: ASTM F3116/F3116M–15, Section 4.1.4 FAA 4.1.4: ‘‘Appendix X1 through appendix X4 provide, within the limitations specified within the appendix, a simplified means of compliance with several of the requirements set forth in 4.2 to 4.26 and 7.1 to 7.9 that can be applied as one (but not the only) means to comply. If the simplified methods in appendix X1 through appendix X3 are used, they must be used together in their entirety.’’ FAA 4.10.1.1: ‘‘In condition A, assume 100% of the semispan wing airload acts on one side of the airplane and 75% of this load acts on the other side. For airplanes with maximum weight of 1,000 pounds or less, 70% of the load acts on the other side.’’ sradovich on DSK3GMQ082PROD with RULES ASTM F3116/F3116M–15, Section 4.10.1.1. 3 Ref 81 FR 96572, December 30, 2016. VerDate Sep<11>2014 22:27 May 10, 2018 Jkt 244001 4 See https://www.faa.gov/aircraft/air_cert/ design_approvals/small_airplanes/small_airplanes_ regs/. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\11MYR1.SGM 11MYR1 21852 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Rules and Regulations Replace: With: ASTM F3116/F3116M–15, Section X1.1.1 FAA X1.1.1: ‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compliance and can only be applied to low-speed, level 1 and level 2 airplanes.’’ X1.1.4 through X1.1.4.5: Same as published in F3116/F3116M–15. Add FAA X1.1.4.6: ‘‘Wings with winglets, tip tanks, or tip fins.’’ ASTM F3116/F3116M–15, Section X1.1.4 23.2220: ASTM F3264–17, section 6.5 23.2225: ASTM F3264–17, section 6.6, combined with the changes in the following table: Replace: With: ASTM F3116/F3116M–15, Section X2.1.1 FAA X2.1.1: ‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compliance and can only be applied to low-speed, level 1 and level 2 airplanes.’’ FAA X3.1.1: ‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compliance and can only be applied to low-speed, level 1 and level 2 airplanes.’’ FAA X4.1.1: ‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compliance and can only be applied to low-speed, level 1 airplanes.’’ ASTM F3116/F3116M–15, Section X3.1.1 ASTM F3116/F3116M–15, Section X4.1.1 23.2230: ASTM F3264–17, section 6.7 23.2235: ASTM F3264–17, section 6.8, combined with the changes in the following table: Replace: With: ASTM F3264–17, Section 6.8.1 ............... FAA 6.8.1: ‘‘F3114–15 Standard Specification for Structures’’. 23.2240: ASTM F3264–17, section 6.9, combined with the changes in the following table: Replace: With: ASTM F3115/F3115M–15, Section 4.4.1 FAA 4.4.1: ‘‘For metallic (aluminum), unpressurized, non-aerobatic, low-speed, level 1 airplanes, applicants can demonstrate a 10,000 hour safe-life by limiting the ‘1g’ gross stress, at maximum takeoff weight, to no more than 5.5 ksi. The applicant must show effective stress concentration factors of 4 or less in highly loaded joints and use materials or material systems for which the physical and mechanical properties are well established.’’ FAA 6.1: ‘‘For bonded airframe structure, the residual strength of bonded joints shall be addressed as follows: For any bonded joint, the failure of which would result in catastrophic loss of the airplane, the limit load capacity must be substantiated by one of the following methods.’’ ASTM F3115/F3115M–15, Section 6.1 .... 23.2245: ASTM F3264–17, section 6.10 23.2250: ASTM F3264–17, section 6.11 23.2255: ASTM F3264–17, section 6.12 23.2260: ASTM F3264–17, section 6.13 23.2265: ASTM F3264–17, section 6.14 23.2270: ASTM F3264–17, section 6.15 Subpart D—Design and Construction 23.2300: ASTM F3264–17, section 7.1, combined with the changes in the following table: sradovich on DSK3GMQ082PROD with RULES Replace: With: ASTM F3232/F3232M–17, Table 1, Row 4.4.6. FAA Table 1, Row 4.4.6: A white circle (‘‘o’’) in the following Aircraft Type Code (ATC) character fields: ‘‘Airworthiness Level—1’’ and ‘‘Stall Speed—L’’; a mark-out (‘‘x’’) in the following ATC character field: ‘‘Number of Engines—M’’; and no codes in any other ATC character field. Note: This change applies the standard of ASTM F3232/F3232M–17, Section 4.4.6, to all single-engine airplanes except level 1 airplanes with a stall speed of 45 knots or less. VerDate Sep<11>2014 22:27 May 10, 2018 Jkt 244001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\11MYR1.SGM 11MYR1 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Rules and Regulations 21853 23.2325: ASTM F3264–17, section 7.6, combined with the changes in the following table: 23.2305: ASTM F3264–17, section 7.2 23.2315: ASTM F3264–17, section 7.4 23.2320: ASTM F3264–17, section 7.5 Replace: With: ASTM F3061/F3061M–17, Section 10.3.2 FAA 10.3.2: ‘‘In each area where flammable fluids or vapors might escape by leakage of a fluid system, there must be means to minimize the probability of ignition of the fluids and vapors, and the resultant hazard if ignition does occur. These means must account for the factors prescribed in 10.3.3 through 10.3.7.’’ 23.2330: ASTM F3264–17, section 7.7 23.2335: ASTM F3264–17, section 7.8 Subpart E—Powerplant 23.2400: ASTM F3264–17, section 8.1, combined with the changes in the following table: Replace: With: ASTM F3065/F3065M–15, Section 4.3 .... An FAA-accepted means of compliance for § 23.2400(c), such as the provisions of § 23.905(d), amendment 23–59. 23.2405: ASTM F3264–17, section 8.2 23.2410: ASTM F3264–17, section 8.3, combined with the changes in the following table: Replace: With: ASTM F3264–17, Section 8.3 .................. 8.3 through 8.3.2: Same as published in F3264–17. Renumber 8.3.3 to 8.3.6. Add FAA 8.3.3 through 8.3.5, and FAA 8.3.7: 8.3.3: ‘‘F3063/F3063M—16a Standard Specification for Design and Integration of Fuel/Energy Storage and Delivery System Installations for Aeroplanes’’. 8.3.4: ‘‘F3064/F3064M—15 Standard Specification for Control, Operational Characteristics and Installation of Instruments and Sensors of Propulsion Systems’’. 8.3.5: ‘‘F3065/F3065M—15 Standard Specification for Installation and Integration of Propeller System’’. 8.3.7: ‘‘F3117—15 Standard Specification for Crew Interface in Aircraft’’. 23.2415: ASTM F3264–17, section 8.4, combined with the changes in the following table: Replace: With: ASTM F3264–17, Section 8.4 .................. 8.4 through 8.4.1: Same as published in F3264–17. Renumber 8.4.2 to 8.4.3. Add FAA 8.4.2: F3063/F3063M—‘‘16a Standard Specification for Design and Integration of Fuel/Energy Storage and Delivery System Installations for Aeroplanes’’. An FAA-accepted means of compliance for the induction system ice protection aspects of § 23.2415, such as the provisions of § 23.1093(a), amendment 23–51. FAA 5.2.1.1: ‘‘Operate throughout its flight power range, including minimum descent idle speeds, in the icing and snow conditions specified in Specification F3120/F3120M, without the accumulation of ice on engine, inlet system components, or airframe components that would do any of the following:’’ [Remove] FAA 5.2.2: ‘‘Each turbine engine must idle for 30 min on the ground, with the air bleed available for engine icing protection at its critical condition, without adverse effect, in the ground icing conditions specified in Specification F3120/F3120M.’’ FAA 5.2.2.1 Followed by momentary operation at takeoff power or thrust. FAA 5.2.2.2 During the 30 min of idle operation, the engine may be run up periodically to a moderate power or thrust setting.’’ ASTM F3066/F3066M–15, Section 5.1 .... ASTM F3066/F3066M–15, Section 5.2.1.1. sradovich on DSK3GMQ082PROD with RULES ASTM F3066/F3066M–15, Section 5.2.2 ASTM F3066/F3066M–15, Sections 5.2.3, 5.2.3.1, and 5.2.3.2. VerDate Sep<11>2014 22:27 May 10, 2018 Jkt 244001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\11MYR1.SGM 11MYR1 21854 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Rules and Regulations 23.2420: ASTM F3264–17, section 8.5, combined with the changes in the following table: Replace: With: ASTM F3264–17, Section 8.5 .................. 8.5 through 8.5.1: Same as published in F3264–17. Remove 8.5.2 and 8.5.3. Add FAA 8.5.2: F3065/F3065M—‘‘15 Standard Specification for Installation and Integration of Propeller System’’. 23.2425: ASTM F3264–17, section 8.6, combined with the changes in the following table: Replace: With: ASTM F3264–17, Section 8.6 .................. 8.6 through 8.6.2: Same as published in F3264–17. Renumber 8.6.3 to 8.6.4. Add FAA 8.6.3 and FAA 8.6.5: 8.6.3: ‘‘F3065/F3065M—15 Standard Specification for Installation and Integration of Propeller System’’. 8.6.5: ‘‘F3117—15 Standard Specification for Crew Interface in Aircraft’’. 23.2430: ASTM F3264–17, section 8.7, combined with the changes in the following table: Replace: With: ASTM F3264–17, Section 8.7 .................. 8.7.1 through 8.7.5: Same as published in F3264–17. Add an FAA-accepted means of compliance for the fuel supply aspects of § 23.2430, such as the provisions of § 23.991(b), amendment 23–43. An FAA-accepted means of compliance for the fuel/oil tank aspects of § 23.2430, such as the provisions of § 23.967(d), amendment 23–43. ASTM F3066/F3066M–15, Section 6.3 .... 23.2435: ASTM F3264–17, section 8.8 23.2440: ASTM F3264–17, section 8.9, combined with the changes in the following table: Replace: With: ASTM Section 8.9, F3264–17 .................. 8.9 through 8.9.2: Same as published in F3264–17. Renumber 8.9.3 to 8.9.4. Renumber 8.9.4 to 8.9.5 and change to, ‘‘F3066/F3066M–15 Standard Specification for Powerplant Systems Specific Hazard Mitigation.’’ Add FAA 8.9.3: 8.9.3: ‘‘F3063/F3063M–16a Standard Specification for Design and Integration of Fuel/Energy Storage and Delivery System Installations for Aeroplanes.’’ Subpart F—Equipment 23.2500: ASTM F3264–17, section 9.1 23.2505: ASTM F3264–17, section 9.2 23.2510: ASTM F3264–17, section 9.3 23.2515: ASTM F3264–17, section 9.4 23.2520: ASTM F3264–17, section 9.5 23.2525: ASTM F3264–17, section 9.6 23.2530: ASTM F3264–17, section 9.7 23.2535: ASTM F3264–17, section 9.8 23.2540: ASTM F3264–17, section 9.9 23.2545: ASTM F3264–17, section 9.10 23.2550: ASTM F3061/F3061M–17, section 10.9 Subpart G—Flightcrew Interface and Other Information 23.2600: ASTM F3264–17, section 10.1, combined with the changes in the following table: sradovich on DSK3GMQ082PROD with RULES Replace: With: ASTM Section 10.1, F3264–17 ................ 10.1.1 through 10.1.5: Same as published in F3264–17. Add an FAA-accepted means of compliance for the windshield luminous transmittance aspects of § 23.2600, such as the provisions of § 23.775(e), amendment 23–49. Add an FAA-accepted means of compliance for the pilot compartment view with formation of fog or frost aspects of § 23.2600, such as the provisions of § 23.773(b), amendment 23–45. VerDate Sep<11>2014 22:27 May 10, 2018 Jkt 244001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\11MYR1.SGM 11MYR1 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Rules and Regulations 23.2605: ASTM F3264–17, section 10.2 23.2610: ASTM F3264–17, section 10.3 21855 23.2615: ASTM F3264–17, section 10.4, combined with the changes in the following table: Replace: With: ASTM Section 6, F3064/F3064M–15 ....... An FAA-accepted means of compliance for the powerplant instruments aspects of § 23.2615, such as the provisions of § 23.1305, amendment 23–52. 23.2620: ASTM F3264–17, sections 5.15 and 10.5 Editorial, Reapproval, Revision Or Withdrawal The FAA expects a suitable consensus standard to be reviewed periodically. ASTM policy is that a consensus standard should be reviewed in its entirety by the responsible subcommittee and must be balloted for reapproval, revision, or withdrawal, within five years of its last approval date. ASTM reapproves a standard— denoted by the year of reapproval in parentheses (e.g., F2427–05a(2013))—to indicate completion of a review cycle with no technical changes made to the standard. ASTM issues editorial changes—denoted by a superscript epsilon in the standard designation (F3235–17 ε1)—to correct information that does not change the meaning or intent of a standard. Any MOC accepted by this document that is based on a standard later reapproved or editorially changed is also considered accepted without the need for a NOA. ASTM revises a standard to make changes to its technical content. Revisions to consensus standards serving as the basis for MOC accepted by this document will not be automatically accepted and will require further FAA acceptance in order for the revisions to be an accepted MOC. sradovich on DSK3GMQ082PROD with RULES Availability ASTM Standard F3264–17, ‘‘Standard Specification for Normal Category Aeroplanes Certification,’’ is available for online reading at https:// www.astm.org/READINGLIBRARY/. ASTM International copyrights these consensus standards and charges the public a fee for service. Individual downloads or reprints of a standard (single or multiple copies, or special compilations and other related technical information) may be obtained through www.astm.org or by contacting ASTM at (610) 832–9585 (phone), (610) 832–9555 (fax), or through service@astm.org (email). To inquire about consensus standard content and/or membership or about ASTM Offices abroad, contact Joe Koury, Staff Manager for Committee F44 on General Aviation: (610) 832–9804, jkoury@astm.org. VerDate Sep<11>2014 22:27 May 10, 2018 Jkt 244001 The FAA maintains a list of accepted MOCs on the FAA website at https:// www.faa.gov/aircraft/air_cert/design_ approvals/small_airplanes/small_ airplanes_regs/. Issued in Kansas City, Missouri, on May 3, 2018. Pat Mullen, Manager, Small Airplanes Standards Branch, Aircraft Certification Service. [FR Doc. 2018–09990 Filed 5–10–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0775; Product Identifier 2017–NM–048–AD; Amendment 39–19272; AD 2018–09–15] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: of certain publications listed in this AD as of June 15, 2018. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of January 3, 2017 (81 FR 90961, December 16, 2016). ADDRESSES: For service information identified in this final rule, contact ˆ Bombardier, Inc., 400 Cote-Vertu Road ´ West, Dorval, Quebec H4S 1Y9, Canada; telephone: 514–855–5000; fax: 514– 855–7401; email: thd.crj@ aero.bombardier.com; internet: http:// www.bombardier.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206– 231–3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0775. 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– 0775; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone: 800–647– 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516–228–7329; fax: 516–794–5531. SUPPLEMENTARY INFORMATION: We are superseding Airworthiness Directive (AD) 2016–25– 18, which applied to certain Bombardier, Inc., Model BD–700–1A10 and BD–700–1A11 airplanes. AD 2016– 25–18 required an inspection for discrepancies of the attachment points of the links between the engine rear mount assemblies, and corrective actions if necessary. This AD requires an inspection of certain attachment points, corrective action if necessary, and replacement of certain bolts and nuts in the engine rear mount assemblies. This AD also adds airplanes to the applicability. This AD was prompted by the determination that replacement of certain nuts and bolts in the engine rear mount assemblies is necessary. We are issuing this AD to address the unsafe condition on these products. Discussion This AD is effective June 15, 2018. The Director of the Federal Register approved the incorporation by reference We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2016–25–18, Amendment 39–18744 (81 FR 90961, SUMMARY: DATES: PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\11MYR1.SGM 11MYR1

Agencies

[Federal Register Volume 83, Number 92 (Friday, May 11, 2018)]
[Rules and Regulations]
[Pages 21850-21855]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09990]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Notice No. 23-18-01-NOA]


Accepted Means of Compliance; Airworthiness Standards: Normal 
Category Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notification of availability; request for comments.

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SUMMARY: This document announces the availability of 63 Means of 
Compliance (MOC) based on 30 published ASTM International (ASTM) 
consensus standards developed by ASTM Committee F44 on General Aviation 
Aircraft. A total of 46 of these accepted MOCs consist of ASTM 
consensus standards as published, with the remaining 17 MOCs comprised 
of a combination of ASTM standards and FAA changes. The Administrator 
finds these MOCs to be an acceptable means, but not the only means, of 
showing compliance to the applicable regulations in part 23, amendment 
23-64, for normal category airplanes. The Administrator further finds 
that these accepted means of complying with part 23, amendment 23-64, 
provide at least the same level of safety as the corresponding 
requirements in part 23, amendment 23-63.

DATES: Comments must be received on or before July 10, 2018.

ADDRESSES: Mail comments to: Federal Aviation Administration, Policy 
and Innovation Division, Small Airplane Standards Branch, AIR-690, 
Attention: Steve Thompson, 901 Locust Street, Room 301, Kansas City, 
Missouri 64106. Comments may also be emailed to: 
[email protected]. Specify the MOC, and if applicable, the 
standard being addressed by designation and title. Mark all comments: 
Part 23 MOC Comments.

FOR FURTHER INFORMATION CONTACT: Steve Thompson, Federal Aviation 
Administration, Policy and Innovation Division, Small Airplane 
Standards Branch, AIR-690, 901 Locust Street, Room 301, Kansas City, 
Missouri 64106; telephone (816) 329-4126; facsimile: (816) 329-4090; 
email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    Interested persons are invited to submit written comments, data, or 
views. Communications should identify the MOC and consensus standard 
number, where applicable, and be submitted to the address previously 
specified in the ADDRESSES section of this NOA. The most helpful 
comments reference a specific portion of the accepted MOC(s) or 
standard(s), explain the reason for any recommended change, and include 
supporting data. The FAA may forward communications regarding the 
consensus standards to ASTM Committee F44 for consideration. The MOC or 
standard may be revised based on received comments. The FAA will 
consider all comments received during the recurring review of the MOC 
and consensus standard and will participate in the consensus standard 
revision process.

Background

    Under the provisions of the National Technology Transfer and 
Advancement Act of 1995 \1\ and Office of Management and Budget (OMB) 
Circular A-119, ``Federal Participation in the Development and Use of 
Voluntary Consensus Standards and in Conformity Assessment 
Activities,'' effective January 27, 2016, the FAA participates in the 
development of consensus standards and uses consensus standards as a 
means of carrying out its policy objectives where appropriate.
---------------------------------------------------------------------------

    \1\ Ref Public Law 104-113 as amended by Public Law 107-107.
---------------------------------------------------------------------------

    Consistent with the Small Airplane Revitalization Act of 2013,\2\ 
the FAA has been working with industry and other stakeholders through 
ASTM to develop consensus standards for use as a MOC in certificating 
small airplanes under part 23. In promulgating part 23, amendment 23-
64, the FAA explained that if it determined such consensus standards 
were acceptable MOC to part 23, it would publish a notice of 
availability of those consensus standards in the Federal Register.
---------------------------------------------------------------------------

    \2\ Ref Public Law 113-53.
---------------------------------------------------------------------------

    Pursuant to FAA Advisory Circular 23.2010-1, section 3.1.1, this 
document serves as a formal acceptance by the Administrator, of MOCs 
based on consensus standards developed by ASTM. The MOCs accepted by 
this document are one means, but not the only means of complying with 
part 23 regulatory requirements.
    The FAA has reviewed the consensus standards referenced in this NOA 
as the basis for MOCs to the regulatory requirements of part 23, 
amendment 23-64. In some cases, the Administrator finds sections of 
ASTM Standard F3264-17, ``Standard Specification for Normal Category 
Aeroplanes Certification,'' without changes, are accepted as means of 
complying with the airworthiness requirements of part 23, without 
degrading safety, and within the scope and applicability of the 
consensus standards. In other cases, the MOCs, while based on ASTM 
consensus standards, include additional FAA provisions necessary to 
comply with the airworthiness requirements of part 23, amendment 23-64.
    Part 23, amendment 23-64, established airworthiness requirements 
based on the level of safety of

[[Page 21851]]

amendment 23-63 regulations, except for areas addressing loss of 
control and icing where the safety level was increased.\3\ Achieving 
this level of safety through compliance with amendment 23-64--for a 
given certification project--may require use of additional MOCs beyond 
those accepted by this document, depending on the details of the 
specific design. For example, an applicant's design may include 
features that are customary, but not addressed in the MOCs accepted by 
this document. Designs may also include features that are innovative 
and not type certificated previously. In either case, a supplemental 
MOC beyond those accepted in this document would be required. For 
example, the MOCs accepted by this document do not contain provisions 
addressing powered-trim system runaways. Therefore, in order to 
maintain the level of safety of amendment 23-63 regulations, applicants 
proposing use of these MOCs for an airplane with a powered-trim system 
would need to supplement the accepted MOC(s) with additional means for 
Sec.  23.2300 to demonstrate safe controllability after a probable trim 
system runaway. To do this, applicants could use the provisions of 
Sec.  23.677(d), amendment 23-49, or other MOC(s) accepted under Sec.  
23.2010. Further information on supplemental MOCs is provided in a part 
23 means of compliance summary table and in the Small Airplanes Issues 
List, which are available on the Small Airplanes--Regulations, Policies 
& Guidance website.\4\
---------------------------------------------------------------------------

    \3\ Ref 81 FR 96572, December 30, 2016.
    \4\ See https://www.faa.gov/aircraft/air_cert/design_approvals/small_airplanes/small_airplanes_regs/.
---------------------------------------------------------------------------

Means of Compliance Accepted in This Document

    The following is a list of sections from part 23, amendment 23-64, 
followed by their corresponding MOC accepted by this document:
23.1457: ASTM F3264-17, section 9.12
23.1459: ASTM F3264-17, section 9.13
23.1529: ASTM F3264-17, section 10.6

Subpart B--Flight

23.2100: ASTM F3264-17, section 5.1
23.2105: ASTM F3264-17, section 5.2
23.2110: ASTM F3264-17, section 5.3
23.2115: ASTM F3264-17, section 5.4
23.2120: ASTM F3264-17, section 5.5
23.2125: ASTM F3264-17, section 5.6
23.2130: ASTM F3264-17, section 5.7
23.2135: ASTM F3264-17, section 5.8, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3173/F3173M-17, Sections 4.9.1.1 and 4.9.1.2...  FAA 4.9.1.1 and
                                                        4.9.1.2:
                                                       4.9.1.1: ``For a
                                                        level 1 or 2
                                                        airplane, or
                                                        level 3 or 4
                                                        airplane of
                                                        6,000 pounds or
                                                        less maximum
                                                        weight, 5
                                                        seconds from
                                                        initiation of
                                                        roll and''
                                                          4.9.1.2: ``For
                                                           a level 3 or
                                                           4 airplane of
                                                           over 6,000
                                                           pounds
                                                           maximum
                                                           weight,
                                                           (W+500)/1300
                                                           seconds, but
                                                           not more than
                                                           10 seconds,
                                                           where W is
                                                           the weight in
                                                           pounds.''
ASTM F3173/F3173M-17, Sections 4.9.3.1 and 4.9.3.2...  FAA 4.9.3.1 and
                                                        4.9.3.2:
                                                       4.9.3.1: ``For a
                                                        level 1 or 2
                                                        airplane, or
                                                        level 3 or 4
                                                        airplane of
                                                        6,000 pounds or
                                                        less maximum
                                                        weight, 4
                                                        seconds from
                                                        initiation of
                                                        roll and''
                                                          4.9.3.2: ``For
                                                           a level 3 or
                                                           4 airplane of
                                                           over 6,000
                                                           pounds
                                                           maximum
                                                           weight,
                                                           (W+2,800)/
                                                           2,200
                                                           seconds, but
                                                           not more than
                                                           7 seconds,
                                                           where W is
                                                           the weight in
                                                           pounds.''
------------------------------------------------------------------------

23.2140: ASTM F3264-17, section 5.9
23.2145: ASTM F3264-17, section 5.10
23.2150: ASTM F3264-17, section 5.11
23.2155: ASTM F3264-17, section 5.12
23.2160: ASTM F3264-17, section 5.13
23.2165: ASTM F3264-17, section 5.14

Subpart C--Structures

23.2200: ASTM F3264-17, Section 6.1, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3116/F3116M-15, Section 5.1.3.1(1).............  FAA 5.1.3.1(1):
                                                       ``VS is a 1g
                                                        computed
                                                        stalling speed
                                                        with flaps
                                                        retracted
                                                        (normally based
                                                        on the maximum
                                                        airplane normal
                                                        force
                                                        coefficient,
                                                        CNA) at the
                                                        design maximum
                                                        takeoff
                                                        weight.''
------------------------------------------------------------------------

23.2210: ASTM F3264-17, section 6.3
23.2215: ASTM F3264-17, section 6.4, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3116/F3116M-15, Section 4.1.4..................  FAA 4.1.4:
                                                       ``Appendix X1
                                                        through appendix
                                                        X4 provide,
                                                        within the
                                                        limitations
                                                        specified within
                                                        the appendix, a
                                                        simplified means
                                                        of compliance
                                                        with several of
                                                        the requirements
                                                        set forth in 4.2
                                                        to 4.26 and 7.1
                                                        to 7.9 that can
                                                        be applied as
                                                        one (but not the
                                                        only) means to
                                                        comply. If the
                                                        simplified
                                                        methods in
                                                        appendix X1
                                                        through appendix
                                                        X3 are used,
                                                        they must be
                                                        used together in
                                                        their
                                                        entirety.''
ASTM F3116/F3116M-15, Section 4.10.1.1...............  FAA 4.10.1.1:
                                                       ``In condition A,
                                                        assume 100% of
                                                        the semispan
                                                        wing airload
                                                        acts on one side
                                                        of the airplane
                                                        and 75% of this
                                                        load acts on the
                                                        other side. For
                                                        airplanes with
                                                        maximum weight
                                                        of 1,000 pounds
                                                        or less, 70% of
                                                        the load acts on
                                                        the other
                                                        side.''

[[Page 21852]]

 
ASTM F3116/F3116M-15, Section X1.1.1.................  FAA X1.1.1:
                                                       ``The methods
                                                        provided in this
                                                        appendix provide
                                                        one possible
                                                        means (but not
                                                        the only
                                                        possible means)
                                                        of compliance
                                                        and can only be
                                                        applied to low-
                                                        speed, level 1
                                                        and level 2
                                                        airplanes.''
ASTM F3116/F3116M-15, Section X1.1.4.................  X1.1.4 through
                                                        X1.1.4.5: Same
                                                        as published in
                                                        F3116/F3116M-15.
                                                       Add FAA X1.1.4.6:
                                                       ``Wings with
                                                        winglets, tip
                                                        tanks, or tip
                                                        fins.''
------------------------------------------------------------------------

23.2220: ASTM F3264-17, section 6.5
23.2225: ASTM F3264-17, section 6.6, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3116/F3116M-15, Section X2.1.1.................  FAA X2.1.1:
                                                       ``The methods
                                                        provided in this
                                                        appendix provide
                                                        one possible
                                                        means (but not
                                                        the only
                                                        possible means)
                                                        of compliance
                                                        and can only be
                                                        applied to low-
                                                        speed, level 1
                                                        and level 2
                                                        airplanes.''
ASTM F3116/F3116M-15, Section X3.1.1.................  FAA X3.1.1:
                                                       ``The methods
                                                        provided in this
                                                        appendix provide
                                                        one possible
                                                        means (but not
                                                        the only
                                                        possible means)
                                                        of compliance
                                                        and can only be
                                                        applied to low-
                                                        speed, level 1
                                                        and level 2
                                                        airplanes.''
ASTM F3116/F3116M-15, Section X4.1.1.................  FAA X4.1.1:
                                                       ``The methods
                                                        provided in this
                                                        appendix provide
                                                        one possible
                                                        means (but not
                                                        the only
                                                        possible means)
                                                        of compliance
                                                        and can only be
                                                        applied to low-
                                                        speed, level 1
                                                        airplanes.''
------------------------------------------------------------------------

23.2230: ASTM F3264-17, section 6.7
23.2235: ASTM F3264-17, section 6.8, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3264-17, Section 6.8.1.........................  FAA 6.8.1:
                                                       ``F3114-15
                                                        Standard
                                                        Specification
                                                        for
                                                        Structures''.
------------------------------------------------------------------------

23.2240: ASTM F3264-17, section 6.9, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3115/F3115M-15, Section 4.4.1..................  FAA 4.4.1:
                                                       ``For metallic
                                                        (aluminum),
                                                        unpressurized,
                                                        non-aerobatic,
                                                        low-speed, level
                                                        1 airplanes,
                                                        applicants can
                                                        demonstrate a
                                                        10,000 hour safe-
                                                        life by limiting
                                                        the `1g' gross
                                                        stress, at
                                                        maximum takeoff
                                                        weight, to no
                                                        more than 5.5
                                                        ksi. The
                                                        applicant must
                                                        show effective
                                                        stress
                                                        concentration
                                                        factors of 4 or
                                                        less in highly
                                                        loaded joints
                                                        and use
                                                        materials or
                                                        material systems
                                                        for which the
                                                        physical and
                                                        mechanical
                                                        properties are
                                                        well
                                                        established.''
ASTM F3115/F3115M-15, Section 6.1....................  FAA 6.1:
                                                       ``For bonded
                                                        airframe
                                                        structure, the
                                                        residual
                                                        strength of
                                                        bonded joints
                                                        shall be
                                                        addressed as
                                                        follows: For any
                                                        bonded joint,
                                                        the failure of
                                                        which would
                                                        result in
                                                        catastrophic
                                                        loss of the
                                                        airplane, the
                                                        limit load
                                                        capacity must be
                                                        substantiated by
                                                        one of the
                                                        following
                                                        methods.''
------------------------------------------------------------------------

23.2245: ASTM F3264-17, section 6.10
23.2250: ASTM F3264-17, section 6.11
23.2255: ASTM F3264-17, section 6.12
23.2260: ASTM F3264-17, section 6.13
23.2265: ASTM F3264-17, section 6.14
23.2270: ASTM F3264-17, section 6.15

Subpart D--Design and Construction

23.2300: ASTM F3264-17, section 7.1, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3232/F3232M-17, Table 1, Row 4.4.6.............  FAA Table 1, Row
                                                        4.4.6:
                                                       A white circle
                                                        (``o'') in the
                                                        following
                                                        Aircraft Type
                                                        Code (ATC)
                                                        character
                                                        fields:
                                                        ``Airworthiness
                                                        Level--1'' and
                                                        ``Stall Speed--
                                                        L''; a mark-out
                                                        (``x'') in the
                                                        following ATC
                                                        character field:
                                                        ``Number of
                                                        Engines--M'';
                                                        and no codes in
                                                        any other ATC
                                                        character field.
                                                       Note: This change
                                                        applies the
                                                        standard of ASTM
                                                        F3232/F3232M-17,
                                                        Section 4.4.6,
                                                        to all single-
                                                        engine airplanes
                                                        except level 1
                                                        airplanes with a
                                                        stall speed of
                                                        45 knots or
                                                        less.
------------------------------------------------------------------------


[[Page 21853]]

23.2305: ASTM F3264-17, section 7.2
23.2315: ASTM F3264-17, section 7.4
23.2320: ASTM F3264-17, section 7.5
23.2325: ASTM F3264-17, section 7.6, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3061/F3061M-17, Section 10.3.2.................  FAA 10.3.2:
                                                       ``In each area
                                                        where flammable
                                                        fluids or vapors
                                                        might escape by
                                                        leakage of a
                                                        fluid system,
                                                        there must be
                                                        means to
                                                        minimize the
                                                        probability of
                                                        ignition of the
                                                        fluids and
                                                        vapors, and the
                                                        resultant hazard
                                                        if ignition does
                                                        occur. These
                                                        means must
                                                        account for the
                                                        factors
                                                        prescribed in
                                                        10.3.3 through
                                                        10.3.7.''
------------------------------------------------------------------------

23.2330: ASTM F3264-17, section 7.7
23.2335: ASTM F3264-17, section 7.8

Subpart E--Powerplant

23.2400: ASTM F3264-17, section 8.1, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3065/F3065M-15, Section 4.3....................  An FAA-accepted
                                                        means of
                                                        compliance for
                                                        Sec.
                                                        23.2400(c), such
                                                        as the
                                                        provisions of
                                                        Sec.
                                                        23.905(d),
                                                        amendment 23-59.
------------------------------------------------------------------------

23.2405: ASTM F3264-17, section 8.2
23.2410: ASTM F3264-17, section 8.3, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3264-17, Section 8.3...........................  8.3 through
                                                        8.3.2: Same as
                                                        published in
                                                        F3264-17.
                                                       Renumber 8.3.3 to
                                                        8.3.6.
                                                       Add FAA 8.3.3
                                                        through 8.3.5,
                                                        and FAA 8.3.7:
                                                       8.3.3: ``F3063/
                                                        F3063M--16a
                                                        Standard
                                                        Specification
                                                        for Design and
                                                        Integration of
                                                        Fuel/Energy
                                                        Storage and
                                                        Delivery System
                                                        Installations
                                                        for
                                                        Aeroplanes''.
                                                          8.3.4: ``F3064/
                                                           F3064M--15
                                                           Standard
                                                           Specification
                                                           for Control,
                                                           Operational
                                                           Characteristi
                                                           cs and
                                                           Installation
                                                           of
                                                           Instruments
                                                           and Sensors
                                                           of Propulsion
                                                           Systems''.
                                                          8.3.5: ``F3065/
                                                           F3065M--15
                                                           Standard
                                                           Specification
                                                           for
                                                           Installation
                                                           and
                                                           Integration
                                                           of Propeller
                                                           System''.
                                                          8.3.7:
                                                           ``F3117--15
                                                           Standard
                                                           Specification
                                                           for Crew
                                                           Interface in
                                                           Aircraft''.
------------------------------------------------------------------------

23.2415: ASTM F3264-17, section 8.4, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3264-17, Section 8.4...........................  8.4 through
                                                        8.4.1: Same as
                                                        published in
                                                        F3264-17.
                                                       Renumber 8.4.2 to
                                                        8.4.3.
                                                       Add FAA 8.4.2:
                                                       F3063/F3063M--
                                                        ``16a Standard
                                                        Specification
                                                        for Design and
                                                        Integration of
                                                        Fuel/Energy
                                                        Storage and
                                                        Delivery System
                                                        Installations
                                                        for
                                                        Aeroplanes''.
ASTM F3066/F3066M-15, Section 5.1....................  An FAA-accepted
                                                        means of
                                                        compliance for
                                                        the induction
                                                        system ice
                                                        protection
                                                        aspects of Sec.
                                                         23.2415, such
                                                        as the
                                                        provisions of
                                                        Sec.
                                                        23.1093(a),
                                                        amendment 23-51.
ASTM F3066/F3066M-15, Section 5.2.1.1................  FAA 5.2.1.1:
                                                       ``Operate
                                                        throughout its
                                                        flight power
                                                        range, including
                                                        minimum descent
                                                        idle speeds, in
                                                        the icing and
                                                        snow conditions
                                                        specified in
                                                        Specification
                                                        F3120/F3120M,
                                                        without the
                                                        accumulation of
                                                        ice on engine,
                                                        inlet system
                                                        components, or
                                                        airframe
                                                        components that
                                                        would do any of
                                                        the following:''
ASTM F3066/F3066M-15, Section 5.2.2..................  [Remove]
ASTM F3066/F3066M-15, Sections 5.2.3, 5.2.3.1, and     FAA 5.2.2:
 5.2.3.2.                                              ``Each turbine
                                                        engine must idle
                                                        for 30 min on
                                                        the ground, with
                                                        the air bleed
                                                        available for
                                                        engine icing
                                                        protection at
                                                        its critical
                                                        condition,
                                                        without adverse
                                                        effect, in the
                                                        ground icing
                                                        conditions
                                                        specified in
                                                        Specification
                                                        F3120/F3120M.''
                                                       FAA 5.2.2.1
                                                        Followed by
                                                        momentary
                                                        operation at
                                                        takeoff power or
                                                        thrust.
                                                       FAA 5.2.2.2
                                                        During the 30
                                                        min of idle
                                                        operation, the
                                                        engine may be
                                                        run up
                                                        periodically to
                                                        a moderate power
                                                        or thrust
                                                        setting.''
------------------------------------------------------------------------


[[Page 21854]]

23.2420: ASTM F3264-17, section 8.5, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3264-17, Section 8.5...........................  8.5 through
                                                        8.5.1: Same as
                                                        published in
                                                        F3264-17.
                                                       Remove 8.5.2 and
                                                        8.5.3.
                                                       Add FAA 8.5.2:
                                                       F3065/F3065M--
                                                        ``15 Standard
                                                        Specification
                                                        for Installation
                                                        and Integration
                                                        of Propeller
                                                        System''.
------------------------------------------------------------------------

23.2425: ASTM F3264-17, section 8.6, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3264-17, Section 8.6...........................  8.6 through
                                                        8.6.2: Same as
                                                        published in
                                                        F3264-17.
                                                       Renumber 8.6.3 to
                                                        8.6.4.
                                                       Add FAA 8.6.3 and
                                                        FAA 8.6.5:
                                                          8.6.3: ``F3065/
                                                           F3065M--15
                                                           Standard
                                                           Specification
                                                           for
                                                           Installation
                                                           and
                                                           Integration
                                                           of Propeller
                                                           System''.
                                                          8.6.5:
                                                           ``F3117--15
                                                           Standard
                                                           Specification
                                                           for Crew
                                                           Interface in
                                                           Aircraft''.
------------------------------------------------------------------------

23.2430: ASTM F3264-17, section 8.7, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM F3264-17, Section 8.7...........................  8.7.1 through
                                                        8.7.5: Same as
                                                        published in
                                                        F3264-17.
                                                       Add an FAA-
                                                        accepted means
                                                        of compliance
                                                        for the fuel
                                                        supply aspects
                                                        of Sec.
                                                        23.2430, such as
                                                        the provisions
                                                        of Sec.
                                                        23.991(b),
                                                        amendment 23-43.
ASTM F3066/F3066M-15, Section 6.3....................  An FAA-accepted
                                                        means of
                                                        compliance for
                                                        the fuel/oil
                                                        tank aspects of
                                                        Sec.   23.2430,
                                                        such as the
                                                        provisions of
                                                        Sec.
                                                        23.967(d),
                                                        amendment 23-43.
------------------------------------------------------------------------

23.2435: ASTM F3264-17, section 8.8
23.2440: ASTM F3264-17, section 8.9, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM Section 8.9, F3264-17...........................  8.9 through
                                                        8.9.2: Same as
                                                        published in
                                                        F3264-17.
                                                       Renumber 8.9.3 to
                                                        8.9.4.
                                                       Renumber 8.9.4 to
                                                        8.9.5 and change
                                                        to, ``F3066/
                                                        F3066M-15
                                                        Standard
                                                        Specification
                                                        for Powerplant
                                                        Systems Specific
                                                        Hazard
                                                        Mitigation.''
                                                       Add FAA 8.9.3:
                                                          8.9.3: ``F3063/
                                                           F3063M-16a
                                                           Standard
                                                           Specification
                                                           for Design
                                                           and
                                                           Integration
                                                           of Fuel/
                                                           Energy
                                                           Storage and
                                                           Delivery
                                                           System
                                                           Installations
                                                           for
                                                           Aeroplanes.''
------------------------------------------------------------------------

Subpart F--Equipment

23.2500: ASTM F3264-17, section 9.1
23.2505: ASTM F3264-17, section 9.2
23.2510: ASTM F3264-17, section 9.3
23.2515: ASTM F3264-17, section 9.4
23.2520: ASTM F3264-17, section 9.5
23.2525: ASTM F3264-17, section 9.6
23.2530: ASTM F3264-17, section 9.7
23.2535: ASTM F3264-17, section 9.8
23.2540: ASTM F3264-17, section 9.9
23.2545: ASTM F3264-17, section 9.10
23.2550: ASTM F3061/F3061M-17, section 10.9

Subpart G--Flightcrew Interface and Other Information

23.2600: ASTM F3264-17, section 10.1, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM Section 10.1, F3264-17..........................  10.1.1 through
                                                        10.1.5: Same as
                                                        published in
                                                        F3264-17.
                                                       Add an FAA-
                                                        accepted means
                                                        of compliance
                                                        for the
                                                        windshield
                                                        luminous
                                                        transmittance
                                                        aspects of Sec.
                                                         23.2600, such
                                                        as the
                                                        provisions of
                                                        Sec.
                                                        23.775(e),
                                                        amendment 23-49.
                                                       Add an FAA-
                                                        accepted means
                                                        of compliance
                                                        for the pilot
                                                        compartment view
                                                        with formation
                                                        of fog or frost
                                                        aspects of Sec.
                                                         23.2600, such
                                                        as the
                                                        provisions of
                                                        Sec.
                                                        23.773(b),
                                                        amendment 23-45.
------------------------------------------------------------------------


[[Page 21855]]

23.2605: ASTM F3264-17, section 10.2
23.2610: ASTM F3264-17, section 10.3
23.2615: ASTM F3264-17, section 10.4, combined with the changes in the 
following table:

------------------------------------------------------------------------
                       Replace:                              With:
------------------------------------------------------------------------
ASTM Section 6, F3064/F3064M-15......................  An FAA-accepted
                                                        means of
                                                        compliance for
                                                        the powerplant
                                                        instruments
                                                        aspects of Sec.
                                                         23.2615, such
                                                        as the
                                                        provisions of
                                                        Sec.   23.1305,
                                                        amendment 23-52.
------------------------------------------------------------------------

23.2620: ASTM F3264-17, sections 5.15 and 10.5

Editorial, Reapproval, Revision Or Withdrawal

    The FAA expects a suitable consensus standard to be reviewed 
periodically. ASTM policy is that a consensus standard should be 
reviewed in its entirety by the responsible subcommittee and must be 
balloted for reapproval, revision, or withdrawal, within five years of 
its last approval date. ASTM reapproves a standard--denoted by the year 
of reapproval in parentheses (e.g., F2427-05a(2013))--to indicate 
completion of a review cycle with no technical changes made to the 
standard. ASTM issues editorial changes--denoted by a superscript 
epsilon in the standard designation (F3235-17 [egr]\1\)--to correct 
information that does not change the meaning or intent of a standard. 
Any MOC accepted by this document that is based on a standard later 
reapproved or editorially changed is also considered accepted without 
the need for a NOA. ASTM revises a standard to make changes to its 
technical content. Revisions to consensus standards serving as the 
basis for MOC accepted by this document will not be automatically 
accepted and will require further FAA acceptance in order for the 
revisions to be an accepted MOC.

Availability

    ASTM Standard F3264-17, ``Standard Specification for Normal 
Category Aeroplanes Certification,'' is available for online reading at 
https://www.astm.org/READINGLIBRARY/. ASTM International copyrights 
these consensus standards and charges the public a fee for service. 
Individual downloads or reprints of a standard (single or multiple 
copies, or special compilations and other related technical 
information) may be obtained through www.astm.org or by contacting ASTM 
at (610) 832-9585 (phone), (610) 832-9555 (fax), or through 
[email protected] (email). To inquire about consensus standard content 
and/or membership or about ASTM Offices abroad, contact Joe Koury, 
Staff Manager for Committee F44 on General Aviation: (610) 832-9804, 
[email protected].
    The FAA maintains a list of accepted MOCs on the FAA website at 
https://www.faa.gov/aircraft/air_cert/design_approvals/small_airplanes/small_airplanes_regs/.

    Issued in Kansas City, Missouri, on May 3, 2018.
Pat Mullen,
Manager, Small Airplanes Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-09990 Filed 5-10-18; 8:45 am]
 BILLING CODE 4910-13-P