Proposed Primary Category Design Standards; Vertical Aviation Technologies (VAT) Model S-52L Rotorcraft, 48574-48575 [2018-20873]

Download as PDF 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 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: daltland on DSKBBV9HB2PROD with PROPOSALS PART 1271—MISCELLANEOUS FEDERAL HOME LOAN BANK OPERATIONS AND AUTHORITIES 2. Amend § 1271.37 by adding paragraph (d) to read as follows: ■ VerDate Sep<11>2014 17:24 Sep 25, 2018 Jkt 244001 * * * * (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] 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 Federal Aviation Administration, DOT. ACTION: Notice of availability; request for comments. AGENCY: 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. SUMMARY: 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. * BILLING CODE 8070–01–P Accounting, Community development, Credit, Federal home loan banks, Government securities, Housing, Miscellaneous federal home loan bank operations and authorities, Reporting and recordkeeping requirements. ■ § 1271.37 Non-administrative expenses; assessments. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 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: ADDRESSES: 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 subset of regulations for the fuel system that are at amendment levels higher than Amendment 27–0 to provide improved occupant protection. E:\FR\FM\26SEP1.SGM 26SEP1 daltland on DSKBBV9HB2PROD with PROPOSALS Federal Register / Vol. 83, No. 187 / Wednesday, September 26, 2018 / Proposed Rules 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 VerDate Sep<11>2014 17:24 Sep 25, 2018 Jkt 244001 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 PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 48575 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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM); withdrawal. AGENCY: 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 https:// 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: SUMMARY: E:\FR\FM\26SEP1.SGM 26SEP1

Agencies

[Federal Register Volume 83, Number 187 (Wednesday, September 26, 2018)]
[Proposed Rules]
[Pages 48574-48575]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-20873]


=======================================================================
-----------------------------------------------------------------------

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: [email protected].

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 [email protected].

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.

[[Page 48575]]

    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
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.