21850 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Rules and Regulations 
1Ref Public Law 104–113 as amended by Public 
Law 107–107. 
2Ref Public Law 113–53. 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. 
[FR Doc. 2018–10015 Filed 5–10–18; 8:45 am] 
BILLING CODE 3410–22–P 
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. 
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: 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 : 
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
1and 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,
2the 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 
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3Ref 81 FR 96572, December 30, 2016. 4See https://www.faa.gov/aircraft/air _cert/ 
design_ approvals/small_ airplanes/small_ airplanes_
regs/. amendment 23–63 regulations, except 
for areas addressing loss of control and icing where the safety level was increased.
3Achieving 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 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 sec-
onds, 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): 
‘‘VSis a 1g computed stalling speed with flaps retracted (normally based on the maximum air-
plane normal force coefficient, C NA) 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.’’ 
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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.’’ 
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 fac-tors 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 fol-
lows: For any bonded joint, the failure of which would result in catastrophic loss of the air-plane, 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: ‘‘Num-
ber 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-en-
gine airplanes except level 1 airplanes with a stall speed of 45 knots or less. 
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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 § 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’’. 
ASTM F3066/F3066M–15, Section 5.1 .... 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. 
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 fol-lowing:’’ 
ASTM F3066/F3066M–15, Section 5.2.2 [Remove] 
ASTM F3066/F3066M–15, Sections 5.2.3, 
5.2.3.1, and 5.2.3.2.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 mod-
erate power or thrust setting.’’ 
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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. 
ASTM F3066/F3066M–15, Section 6.3 .... An FAA-accepted means of compliance for the fuel/oil tank aspects of § 23.2430, such as the provi-
sions of § 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 
§ 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. 
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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 § 23.2615, s uch 
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. 
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 . 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 
AGENCY : Federal Aviation 
Administration (FAA), Department of Transportation (DOT). 
ACTION : Final rule. 
SUMMARY : 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. 
DATES : This AD is effective June 15, 
2018. 
The Director of the Federal Register 
approved the incorporation by reference 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 Bombardier, Inc., 400 Co ˆte-Vertu Road 
West, Dorval, Que ´bec 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 : 
Discussion 
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, 
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