48574 Federal Register / Vol. 83, No. 187 / Wednesday, September 26, 2018 / Proposed Rules 
institutions whose FICO assessments 
had changed due to amendments to their call reports. FHFA concluded that further assessments are not legally permissible because Congress has authorized FICO to assess FDIC-insured institutions only for three specific purposes—to pay interest on the FICO Obligations, issuance costs, and custodian fees—which means that FICO’s assessment authority does not extend to obtaining monies for paying refunds of prior FICO assessments. FICO also could not use its own assets to provide such monies because, as described previously, FICO has no legal obligation under any statute to reimburse insured institutions for their prior overpayments of FICO assessments, and has no authority to spend its assets for any purposes beyond those authorized by statute. 
Third, FHFA considered whether 
FICO could direct the FDIC, as collection agent, to could continue to process adjustments to prior FICO assessments on its own, but deemed that approach not to be legally permissible. The FDIC acts as FICO’s agent when collecting the FICO assessments, and as such FDIC’s authority derives from, and can be no greater than, FICO’s own assessment authority. 
Solicitation of Comments 
FHFA invites comments on all aspects 
of the supporting information provided 
in this RFA section. 
List of Subjects in 12 CFR Part 1271 
Accounting, Community 
development, Credit, Federal home loan 
banks, Government securities, Housing, Miscellaneous federal home loan bank operations and authorities, Reporting and recordkeeping requirements. 
Authority and Issuance 
Accordingly, for reasons stated in the 
SUPPLEMENTARY INFORMATION and under 
the authority of 12 U.S.C. 1431(a), 
1432(a), 4511(b), 4513, 4526(a), FHFA proposes to amend part 1271 of subchapter D of chapter XII of title 12 of the Code of Federal Regulations as follows: 
PART 1271—MISCELLANEOUS 
FEDERAL HOME LOAN BANK OPERATIONS AND AUTHORITIES 
■1. The authority citation for part 1271 
continues to read as follows: 
Authority: 12 U.S.C. 1430, 1431, 1432, 
1441(b)(8), (c), (j), 1442, 4511(b), 4513(a), 
4526. 
■2. Amend § 1271.37 by adding 
paragraph (d) to read as follows: § 1271.37 Non-administrative expenses; assessments. 
* * * * * 
(d)(1) Final Assessments. All 
Financing Corporation assessments 
collected during 2019 shall be final. Subsequent to March 29, 2019, no insured depository institution shall have any right to receive refunds for any overpayment of any prior Financing Corporation assessments nor shall it be billed for any underpayment of any prior Financing Corporation assessments that arise as a result of an amendment to any Consolidated Reports of Condition and Income on which the prior Financing Corporation assessment had been based. 
(2) Amendments to call reports. 
Amendments to an institution’s Consolidated Reports of Condition and Income for quarters prior to and including the fourth quarter of 2018 shall not affect an institution’s Financing Corporation assessments after March 26, 2019. 
(3) June 2019 Assessment. In the event 
Financing Corporation assessments are collected in June 2019, amendments to an institution’s first quarter 2019 Consolidated Reports of Condition and Income that are submitted after June 25, 2019 shall not affect the institution’s Financing Corporation assessment. 
Dated: September 20, 2018. 
Melvin L. Watt, 
Director, Federal Housing Finance Agency. 
[FR Doc. 2018–20975 Filed 9–25–18; 8:45 am] 
BILLING CODE 8070–01–P 
DEPARTMENT OF TRANSPORTATION 
Federal Aviation Administration 
14 CFR Part 21 
[Docket No. FAA–2018–0860] 
Proposed Primary Category Design 
Standards; Vertical Aviation Technologies (VAT) Model S–52L Rotorcraft 
AGENCY : Federal Aviation 
Administration, DOT. 
ACTION : Notice of availability; request 
for comments. 
SUMMARY : This notice announces the 
existence of and requests comments on the proposed airworthiness design standards for acceptance of the Vertical Aviation Technologies (VAT) Model S– 52L rotorcraft under the regulations for primary category aircraft. 
DATES : Comments must be received on 
or before November 26, 2018. ADDRESSES : Send comments to the 
Federal Aviation Administration, Policy and Innovation Division, Rotorcraft Standards Branch, AIR–681, Attention: Michael Hughlett, 10101 Hillwood Parkway, Fort Worth, Texas 76177. Comments may also be emailed to: Michael.Hughlett@faa.gov. 
FOR FURTHER INFORMATION CONTACT : 
Michael Hughlett, Aviation Safety Engineer, Rotorcraft Standards Branch, Policy and Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone (817) 222–5110; email Michael.Hughlett@faa.gov. 
SUPPLEMENTARY INFORMATION : 
Comments Invited 
The FAA invites interested parties to 
submit comments on the proposed airworthiness standards to the address specified above. Commenters must identify the VAT Model S–52L on all submitted correspondence. The most helpful comments reference a specific portion of the airworthiness standards, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received on or before the closing date before issuing the final acceptance. We will consider comments filed late if it is possible to do so without incurring expense or delay. We may change the proposed airworthiness standards based on received comments. 
Background 
The primary category for aircraft was 
created specifically for the simple, low 
performance personal aircraft. Section 21.17(f) provides a means for applicants to propose airworthiness standards for their particular primary category aircraft. The FAA procedure establishing appropriate airworthiness standards includes reviewing and possibly revising the applicants’ proposal, publication of the submittal in the Federal Register for public review 
and comment, and addressing the comments. After all necessary revisions, the standards are published as approved FAA airworthiness standards. 
Proposed Airworthiness Standards for 
Acceptance Under the Primary Category 
This document prescribes 
airworthiness standards for the issuance of a type certificate for the VAT Model S–52L, a primary category rotorcraft, and its engine. The airworthiness standards for this aircraft include a sub- set of regulations for the fuel system that are at amendment levels higher than Amendment 27–0 to provide improved occupant protection. 
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Each person who applies under part 
21 for a change to this type certificate 
must show compliance with these requirements. 
CAR 13 effective 03/5/1952 as follows: 
13.0, 13.10, 13.11, 13.12, 13.13, 13.14, 
13.16(a), 13.16(b), 13.16(d), 13.17, 13.18, 
13.19, 13.20, 13.21, 13.100, 13.101, 13.102, 13.103, 13.104, 13.110, 13.111, 13.112, 13.113, 13.114, 13.115, 13.150, 13.151, 13.153, 13.155, 13.156, 13.157. 
CAR 13 effective 05/16/1953 as 
follows: 
13.1, 13.15, 13.152, 13.154. 
14 CFR 33 through amendment 33–9 
as follows: 
33.4, Appendix A33. 14 CFR 33 through amendment 33–30 
as follows: 
33.7(b). 14 CFR 27 through amendment 27–0, 
except as noted below: 
•27.853 at amendment 27–37, 
•27.1351 at amendment 27–13, 
•27.1357 at amendment 27–13, 
•27.1529 at amendment 27–18, 
•27.561 is replaced with VAT.561, 
•27.785 is replaced with VAT.785. 
14 CFR 27 through amendment 27–30 
as follows: 
27.952(a), 27.952(c), 27.952(f), 
27.952(g). 
14 CFR 27 through amendment 27–35 
as follows: 
27.975(b). 
VAT.561 General: (a) The rotorcraft, although it may be 
damaged in emergency landing 
conditions on land or water, must be designed as prescribed in this section to protect the occupants under those conditions. 
(b) The structure must be designed to 
give each occupant every reasonable chance of escaping serious injury in a minor crash landing when— 
(1) Proper use is made of seats, belts, 
and other safety design provisions; 
(2) The wheels are retracted (where 
applicable); and 
(3) The occupant experiences the 
following ultimate inertia forces relative to the surrounding structure: 
(i) Upward—4.0g. 
(ii) Forward—8.0g. (iii) Sideward—8.0g. (iv) Downward—12.0g. (v) Rearward—4.0g. (c) The supporting structure must be 
designed to restrain, under any ultimate 
inertial load up to those specified in this paragraph, any item of mass above and/ or behind the crew and passenger compartment that could injure an occupant if it came loose in an emergency landing. Items of mass to be considered include, but are not limited to, rotors, transmissions, and engines. The items of mass must be restrained for the following ultimate inertial load factors: 
(1) Upward—1.5g. 
(2) Forward—4.0g. (3) Sideward—2.0g. (4) Downward—4.0g VAT.785 Seats and berths: (a) The seats and berths, and their 
supporting structures, must be designed 
for loads resulting from the specified flight and landing conditions, including the emergency landing conditions of VAT.561. 
(b) The reactions from safety belts and 
harnesses must be considered. 
(c) Each pilot seat must be designed 
for the reactions resulting from the application of the pilot forces prescribed in Sec. 27.397. 
(d) The structural analysis and testing 
of the structures specified in paragraphs (a) through (c) may be simplified— 
(1) By assuming that the critical load 
in each direction, as determined from the prescribed flight, ground, and emergency landing conditions, acts separately; or 
(2) By using selected combinations of 
loads, if the required strength in the specified directions is proven. 
(e) Each occupant’s seat must have a 
combined safety belt and shoulder harness with a single-point release. Each pilot’s combined safety belt and shoulder harness must allow each pilot, when seated with safety belt and shoulder harness fastened, to perform all functions necessary for flight operations. There must be a means to secure belts and harnesses, when not in use, to prevent interference with the operation of the rotorcraft and with rapid egress in an emergency. 
(f) Each occupant must be protected 
from serious head injury by a safety belt plus a shoulder harness that will prevent the head from contacting any injurious object. 
(g) The safety belt and shoulder 
harness must meet the static strength requirements specified by this rotorcraft type certification basis. 
VAT.963 Fuel tanks: General: 
Each flexible fuel tank bladder or 
liner must be approved or shown to be 
suitable for the particular application and must be puncture-resistant. Puncture resistance must be shown by meeting TSO–C80 paragraph 16.0 requirements using a minimum puncture force of 250 pounds. 
14 CFR 36 through amendment 36–30 
as follows: 
•Subpart H Issued in Fort Worth, Texas, on September 
17, 2018. 
Jorge Castillo, Acting Manager, Rotorcraft Standards 
Branch, Policy and Innovation Division, Aircraft Certification Service. 
[FR Doc. 2018–20873 Filed 9–25–18; 8:45 am] 
BILLING CODE 4910–13–P 
DEPARTMENT OF TRANSPORTATION 
Federal Aviation Administration 
14 CFR Part 39 
[Docket No. FAA–2017–0313; Product 
Identifier 2017–NE–11–AD] 
RIN 2120–AA64 
Airworthiness Directives; CFM 
International S.A. Turbofan Engines 
AGENCY : Federal Aviation 
Administration (FAA), DOT. 
ACTION : Notice of proposed rulemaking 
(NPRM); withdrawal. 
SUMMARY : The FAA withdraws an 
NPRM that published on August 25, 2017 regarding an unsafe condition involving certain CFM International CFM56–7B turbofan engines. The agency subsequently determined that the identified unsafe condition was not adequately addressed by the proposed actions and published two final rules that adequately address the identified unsafe condition. 
DATES : Effective September 26, 2018, the 
FAA withdraws the NPRM published at 82 FR 40516, on August 25, 2017. 
ADDRESSES : You may examine the 
Airworthiness Directive (AD) docket on the internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA–2017– 0313; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this action, the NPRM (82 FR 40516, August 25, 2017) the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is 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 : 
Christopher McGuire, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington MA, 01803; phone: 781–238–7120; fax: 781–238– 7199; email: chris.mcguire@faa.gov. 
SUPPLEMENTARY INFORMATION : 
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