Document ID: FAA-2018-0860-0001
Agency: faa
Document Type: Proposed Rule
Title: Proposed Primary Category Design Standards; Vertical Aviation Technologies Model S-52L Rotorcraft
Posted Date: 2018-09-26T04:00Z

[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]

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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.

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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