[Federal Register Volume 62, Number 25 (Thursday, February 6, 1997)]
[Proposed Rules]
[Pages 5552-5554]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-2960]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 62, No. 25 / Thursday, February 6, 1997 /
Proposed Rules
[[Page 5552]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. 136CE, Special Condition 23-ACE-88]
Special Conditions; Ballistic Recovery Systems Cirrus SR-20
Installation
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed special conditions.
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SUMMARY: This notice proposes special conditions for the type
certification of the Ballistic Recovery Systems, Inc., (BRS) parachute
recovery system installed in the Cirrus SR-20 Model airplane. This
system is referred to as the General Aviation Recovery Device (GARD).
Airplanes modified to use this system will incorporate novel or unusual
design features for which the applicable airworthiness regulations do
not contain adequate or appropriate safety standards. These special
conditions contain the additional airworthiness standards that the
Administrator considers necessary to establish a level of safety
equivalent to the original certification basis for these airplanes.
DATES: Comments must be received on or before March 10, 1997.
ADDRESSES: Comments on this proposal may be mailed in duplicate to:
Federal Aviation Administration, Office of the Assistant Chief Counsel,
ACE-7, Attention: Rules Docket Clerk, Docket No. 136CE, Room 1558, 601
East 12th Street, Kansas City, Missouri 64106. All comments must be
marked: Docket No. 136CE. Comments may be inspected in the Rules Docket
weekdays, except Federal holidays, between 7:30 a.m. and 4:00 p.m.
FOR FURTHER INFORMATION CONTACT: Lowell Foster, Aerospace Engineer,
Standards Office (ACE-110), Small Airplane Directorate, Aircraft
Certification Service, Federal Aviation Administration, 601 East 12th
Street, Kansas City, Missouri 64106; telephone (816) 426-5688.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of
these special conditions by submitting such written data, views, or
arguments as they may desire. Communications should identify the
regulatory docket or notice number and be submitted in duplicate to the
address specified above. All communication received on or before the
closing date for comments specified above will be considered by the
Administrator before taking further rulemaking action on this proposal.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must include a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 136CE.'' The postcard will be date stamped and returned
to the commenter. The proposals contained in this notice may be changed
in light of the comments received. All comments received will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested parties. A report
summarizing each substantive public contact with FAA personnel
concerned with this rulemaking will be filed in the docket.
Background
On March 7, 1996, Cirrus Design, 4515 Taylor Circle, Duluth, MN
55811, filed an application for a type certificate (TC). Included in
this TC application was the provision to install the BRS GARD parachute
recovery system as standard equipment on each Cirrus Model SR-20
airplane. The parachute recovery system is intended to recover an
airplane in emergency situations such as mid-air collision, loss of
engine power, loss of airplane control, severe structural failure,
pilot disorientation, or pilot incapacitation with a passenger on
board. The GARD system, which is only used as a last resort, is
intended to prevent serious injuries to the airplane occupants by
parachuting the airplane to the ground.
The parachute recovery system consists of a parachute packed in a
canister mounted on the airframe. A solid propellant rocket motor
deploys the canopy and is located on the side of the canister. A door
positioned above the canister seals the canister, parachute canopy, and
rocket motor from the elements and provides free exit when the canopy
is deployed. The system is deployed by a mechanical pull handle mounted
so that the pilot and passenger can reach it. At least two separate and
independent actions are required to deploy the system.
A multi-cable bridle attaches the canopy bridle to the airplane
primary structure. The cable lengths are sized to provide the best
airplane touchdown attitude. The cables are routed from the parachute
canister thru the fuselage and run externally to the fuselage attach
points. The external portion of these cables are covered with small
frangible fairings.
Discussion
Special conditions may be issued and amended, as necessary, as part
of the type certification basis if the Administrator finds that the
airworthiness standards designated in accordance with Sec. 21.101(b)(1)
do not contain adequate or appropriate safety standards because of the
novel and unusual design features of the airplane modification. Special
conditions, as appropriate, are issued after public notice in
accordance with Sec. 11.49 (as amended September 25, 1989), as required
by Secs. 11.28 and 11.29(b). The special conditions become part of the
type certification basis, as provided by Sec. 21.17(a)(2).
The installation of parachute recovery systems in 14 CFR part 23
airplanes was not envisioned when the certification basis for these
airplanes was established. In addition, the Administrator has
determined that current regulations do not contain adequate or
appropriate safety standards for a parachute recovery system;
therefore, this system is considered a novel and unusual design
feature. The flight test demonstration requirements will ensure that
the parachute recovery system will perform its intended function
without exceeding its strength capabilities. Demonstrations will be
required to show that the parachute will deploy in specified flight
conditions at both ends of the flight envelope. These conditions are a
high speed deployment and deployment during a one-turn spin entry. If
the airplane is spin resistant,
[[Page 5553]]
the condition is the maneuver that results from pro-spin control inputs
held for one turn, or three seconds, whichever comes first.
Occupant restraint requirements will ensure that the airplane is
equipped with a restraint system designed to protect the occupants from
injury during parachute deployment and ground impact. Each occupant
seat must meet the requirements of 14 CFR part 23, Sec. 23.562 as part
of the original certification basis.
Requirements for parachute performance will ensure all of the
following: (a) The parachute complies with the applicable section of
TSO-C23c (SAE AS8015A) at the maximum airplane weights. (b) The
parachute deployment loads do not exceed the structural strength of the
airplane. (c) The system will provide a ground impact that does not
result in serious injury of the passengers. (d) The system will operate
in adverse weather conditions.
The requirements for the functions and operations of the parachute
recovery system will ensure all of the following: (a) There is no fire
hazard associated with the system. (b) The failure of this system has
to be shown to be extremely improbable. The installation of this system
allows relief from another part 23 requirement, spins. For this reason,
it will need to be a dispatch item and have a high level of
reliability. (c) That the system will work in all adverse weather
conditions that the airplane is approved to operate in, including the
IFR and icing environments. (d) The sequence of arming and activating
the system will prevent inadvertent deployment. (e) The system can be
activated from either the pilot's or the copilot's position by various
sized people. (f) The system will be labeled to show its identification
function and operating limitations. (g) A warning placard will be
located on the fuselage near the rocket motor to warn rescue crews of
the ballistic system. (h) The FAA-approved flight manual will include a
thorough explanation of system's operation and limitations as well as
the safe deployment envelope. (i) The occupants are protected from
serious injury after touchdown in adverse weather.
Requirements for protection of the parachute recovery system will
ensure the following: the system is protected from deterioration due to
weathering, corrosion, and abrasion; provisions are made to provide
adequate ventilation and drainage of the airplane structure that houses
the parachute canister.
Requirements for a system inspection provision will ensure that
adequate means are available to permit examination of the parachute
recovery system components and that instructions for continued
airworthiness are provided.
Requirements for the system to function throughout the entire
operational flight envelope are incorporated because it is reasonable
to expect pilots to deploy the system any time that there is a
catastrophic failure.
Requirements for operating limitations of the parachute recovery
system will ensure that the system operating limitations and deployment
envelope are prescribed, including inspection, repacking, and replacing
the system's parachute deployment mechanism at approved intervals.
Conclusion
This action affects only novel and unusual design features on
specified model/series airplanes. It is not a rule of general
applicability and affects only those applicants who apply to the FAA
for approval of these features on these airplanes.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and symbols.
Citation
The authority citation for this special condition is as follows:
Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and
101; and 14 CFR 11.28 and 11.49
The Proposed Special Conditions
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes the
following special conditions as part of the type certification basis
for the Cirrus Model SR-20 airplanes:
1. Flight Test Demonstration
(a) The system must be demonstrated in flight to satisfactorily
perform its intended function, without exceeding the system deployment
design loads, for the critical flight conditions.
(b) Satisfactory deployment of the parachute must be demonstrated,
at the most critical airplane weight and balance, for the following
flight conditions:
(1) One of the two maneuvers, (i) or (ii), must be performed for
the low speed end of the flight envelope;
(i) Spin with deployment at one turn or 3 seconds, whichever is
longer; or (ii) Deployment immediately following the maneuver that
results from a pro-spin control input held for one turn or 3 seconds,
whichever is longer.
(2) Never exceed speed with 1g normal load.
2. Occupant Restraint
Each seat in the airplane must be equipped with a restraint system,
consisting of a seat belt and shoulder harness, that will protect the
occupants from head and upper torso injuries during parachute
deployment and ground impact at the critical load conditions.
3. Parachute Performance
(a) The parachute must comply with the applicable requirements of
TSO-C23c, or an approved equivalent, for the maximum airplane weight at
paragraph 1(b)(2).
(b) The loads during deployment must not exceed 80 percent of the
ultimate design load for the attaching structure, the cabin structure
surrounding the occupants, and any interconnecting structure of the
airplane.
(c) It must be shown that, although the airplane structure may be
damaged, the airplane impact during touchdown will result in an
occupant environment in which serious injury to the occupants is
improbable.
(d) It must be shown that, with the parachute deployed, the
airplane can impact the ground in various adverse weather conditions,
including winds up to 15 knots, without endangering the airplane
occupants.
4. System Function and Operations
(a) It must be shown that there is no fire hazard associated with
activation of the system.
(b) The system must be shown to perform its intended function and
system failure must be shown to be extremely improbable.
(c) It must be shown that reliable and functional deployment in the
adverse weather conditions that the airplane is approved for have been
considered. For example, if the aircraft is certified for flight into
known icing, and flight test in actual icing reveals that ice may cover
the deployment area, then the possible adverse effects of ice or an ice
layer covering the parachute deployment area should be analyzed.
(d) It must be shown that arming and activating the system can only
be accomplished in a sequence that makes inadvertent deployment
extremely improbable.
(e) It must be demonstrated that the system can be activated
without difficulty by various sized people, from a 10th percentile
female to a 90th percentile male, while sitting in the pilot or copilot
seat.
[[Page 5554]]
(f) The system must be labeled to show its identification,
function, and operating limitations.
(g) A warning placard must be located on the fuselage near the
rocket motor warning of the rocket.
(h) The FAA-approved flight manual must include a thorough
explanation of operation and limitations as well as the safe deployment
envelope.
(i) It must be shown that the occupants will be protected from
serious injury after touchdown under various adverse weather
conditions, including high winds.
5. System Protection
(a) All components of the system must provide protection against
deterioration due to weathering, corrosion, and abrasion.
(b) Adequate provisions must be made for ventilation and drainage
of the parachute canister and associated structure to ensure the sound
condition of the system.
6. System Inspection Provisions
(a) Instructions for continued airworthiness must be prepared for
the system that meet the requirements of Sec. 23.1529.
(b) Adequate means must be provided to permit the close examination
of the parachute and other system components to ensure proper
functioning, alignment, lubrication, and adjustment during the required
inspection of the system.
7. Operating Limitations
(a) Operating limitations must be prescribed to ensure proper
operation of the system within its deployment envelope. A detailed
discussion of the system, including operation, limitations and
deployment envelope must be included in the Airplane Flight Manual.
(b) The deployment envelope of the GARD system must be the same as
the normal operating envelope of the airplane.
(c) Operating limitations must be prescribed for inspecting,
repacking, and replacing the parachute and deployment mechanism at
approved intervals.
Issued in Kansas City, Missouri on January 21, 1997.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-2960 Filed 2-5-97; 8:45 am]
BILLING CODE 4910-13-P
