[Federal Register Volume 62, Number 182 (Friday, September 19, 1997)]
[Proposed Rules]
[Pages 49175-49177]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-25010]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 21
Proposed Airworthiness Standards for Acceptance Under the Primary
Category Rule
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Request for comments.
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SUMMARY: This notice requests comments on proposed airworthiness
standards for acceptance of the Dragonfly Model 333 helicopter under 14
CFR 21.17(f), designation of applicable regulations for primary
category aircraft.
DATES: Comments must be received on or before October 20, 1997.
ADDRESSES: Send all comments to the FAA, Rotorcraft Directorate,
Aircraft Certification Service, Rotorcraft Standards Staff, Fort Worth,
Texas 76193-0110.
FOR FURTHER INFORMATION CONTACT: Scott Horn, Aerospace Engineer,
Rotorcraft Standards Staff (ASW-110), Rotorcraft Directorate, Aircraft
Certification Service, FAA; telephone number (817) 222-5125, fax number
(817) 222-5961.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite interested parties to submit comments on the proposed
airworthiness standards to the address specified above. The FAA will
consider all communications received on or before the closing date
before issuing the final acceptance. The proposed airworthiness
standards and comments received may be inspected at the FAA, Rotorcraft
Directorate, Aircraft Certification Service, Rotorcraft Standards
Staff, 2601 Meacham Blvd., Fort Worth, TX 76137, between the hours of
7:30 a.m. and 4:00 p.m. weekdays, except Federal holidays.
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.
Accordingly, the applicant has submitted a request to the FAA to
include the Italian airworthiness authority's very light rotorcraft
(VLR) rules as part of the primary category rotorcraft rules. The
requester justifies this request by noting that the Italian
airworthiness authority has approved the applicant's aircraft in Italy
under the VLR rules. The FAA has considered the applicant's proposal
and has determined that those 14 CFR part 27 and 33 requirements
equivalent to the Italian VLR rules and certain additional
airworthiness standards should apply.
Proposed Airworthiness Standards for Acceptance Under the Primary
Category Rule (PCR)
PCR.1 Applicability
(a) This document prescribes airworthiness standards for the issue
of a type certificate and changes to that type certificate for the
Dragon Fly Model 333, a Primary Category rotorcraft and its engine.
(b) Each person who applies under part 21 for a change to this
certificate must show compliance with these requirements.
27.2(a), (b), and (c); 27.21; 27.25(a) and (b); 27.27; 27.29; 27.31;
27.33; 27.45(a), (b), (c), and (d); 27.51; 27.71; 27.73(a)(1)(i),
(a)(1)(iii), and (a)(2)(i); 27.75(a)(1), (a)(2)(i), and (a)(3);
27.79(a), and (b)(1); 27.141(a), (b)(2), and (b)(3); 27.143(a), (b),
(d), and (e);
PCR.143(c) A wind direction and velocity must be established in
which the rotorcraft can be operated without loss of control on or near
the ground in any maneuver appropriate to the type including crosswind
takeoffs, sideward flight, and rearward flight with--
(1) Critical weight;
(2) Critical center of gravity;
(3) Critical rotor RPM and
(4) Altitude, from standard sea level conditions to the maximum
altitude capability of the rotorcraft or 7000 feet, whichever is less.
27.151; 27.161; 27.171; 27.173; 27.175; 27.177; 27.231; 27.235; 27.239;
27.241; 27.251; 27.301; 27.305; 27.307; 27.309; 27.321; 27.337; 27.339;
27.341; 27.351; 27.361; 27.391; 27.395; 27.397; 27.399; 27.411; 27.427;
27.471; 27.473; 27.475; 27.477; 27.479; 27.481; 27.483; 27.485; 27.493;
27.497; 27.501; 27.505; 27.521; 27.547; 27.549; 27.561(a), (b)(1), and
(c);
PCR.561(b)(2) Each occupant and each item of mass inside the cabin
that could injure an occupant is restrained when subjected to the
following ultimate inertial load factors relative to the surrounding
structure: (i) Upward--3g. (ii) Forward--9g. (iii) Sideward--3g. (iv)
Downward--9g.
27.571(a), (b), and (c); 27.601; 27.603; 27.605; 27.607; 27.609;
27.611; 27.613(a);
PCR.613(b) The design values must be so chosen that the
probability of any structure being understrength because of material
variations is extremely remote.
(c) Values contained in MIL-HDBK-5, MIL-HDBK-17 Part I, ANC-17 Part
II, ANC-18, MIL-HDBK-23 Part I, and ANC-23 Part II must be used unless
shown to be inapplicable in a particular case.
(d) The strength, detail design, and fabrication of the structure
must minimize the probability of disastrous fatigue failure.
27.619; 27.621; 27.623; 27.625;
PCR.625(d) Each seat and safety belt with harness attachment to
the structure must be shown by analysis, tests, or
[[Page 49176]]
both, to be able to withstand the inertia forces prescribed in
PCR.561(b)(2) multiplied by a fitting factor of 1.33.
27.629; 27.653; 27.659; 27.661; 27.663; 27.671; 27.673; 27.675; 27.679;
27.681; 27.683; 27.685; 27.687; 27.691; 27.723; 27.725; 27.727; 27.731;
27.733; 27.735; 27.737; 27.751; 27.753; 27.755; 27.771; 27.773; 27.777;
27.779; 27.783; 27.785 (a), (b), (c), (e), (f), (g), (h), (i), and (j);
27.787; 27.807 (a), (b), and (c); 27.831; 27.853(a), (b), and (c)(1);
27.855; 27.859(a) and (b); 27.861; 27.863; 27.871; 27.873; 27.901;
PCR.903(a) Engine type certification. The engine must have an
approved type certificate or meet the requirements provided in this
document for the engine. The engine must be qualified in accordance
with 33.49(d) or be otherwise approved for the intended usage.
27.903(b); 27.907; 27.917; 27.921; 27.923(a), (b), (c), (d), (f), (g),
and (l); 27.927; 27.931; 27.935; 27.951; 27.955(a)(1), (2), (3), (4),
(5), (6);
PCR.955(a)(7) The fuel filter required by 27.997 must be blocked
to the degree necessary to provide the highest pressure drop across the
filter prior to the filter going into bypass.
27.955(b) and (c); 27.959; 27.961; 27.963[Amdt. 27-23];
PCR.965 Fuel Tank Tests. Each fuel tank must be able to withstand,
without failure or leakage:
(a) For each conventional metal tank and nonmetallic tank with
walls not supported by the rotorcraft structure, a pressure of 3.5
p.s.i.
(b) For each integral tank, the pressure developed during the
maximum limit acceleration of the rotorcraft with a full tank, with
simultaneous application of the critical limit structure loads.
(c) For each nonmetallic tank with walls supported by the
rotorcraft structure and with actual support conditions, a pressure of
2.0 p.s.i. The supporting structure must be designed for the critical
loads occurring in the flight or landing condition combined with the
fuel pressure loads resulting from the corresponding accelerations.
27.969;
PCR.971 Fuel Tank Sump. (a) Each fuel tank must have a drainable
sump with an effective capacity in any ground attitude to be expected
in service of 0.10 percent of the tank capacity or 120 cc, whichever is
greater, unless--
(1) The fuel system has a sediment bowl or chamber that is
accessible for preflight drainage and has a minimum capacity; and
(2) Each fuel tank drain is located so that in any ground attitude
to be expected in service, water will drain from all parts of the tank
to the sediment bowl or chamber.
(b) Each sump, sediment bowl, and sediment chamber drain required
by this section must comply with the drain provisions of paragraph
27.999(b).
27.973; 27.975; 27.977; 27.991; 27.993; 27.995; 27.997; 27.999;
PCR.1011 Engine Oil System: General.
(a) Each engine must have an independent oil system that can supply
it with the appropriate quantity of oil at a temperature not above that
safe for continuous operation.
(b) The usable capacity of each oil system may not be less than the
product of the endurance of the rotorcraft under critical operating
conditions and the maximum oil consumption of the engine under the same
conditions.
(c) If an engine depends upon a fuel/oil mixture for lubrication,
then a reliable means of providing it with the appropriate mixture must
be established.
27.1013; 27.1015; 27.1017; 27.1019(b); 27.1021; 27.1027; 27.1041;
27.1043; 27.1045; 27.1091; 27.1093; 27.1121; 27.1123; 27.1141; 27.1143;
27.1145; 27.1147; 27.1163; 27.1183; 27.1185; 27.1187; 27.1189; 27.1191;
27.1193(a),(b),(c),(d), and (e); 27.1194; 27.1301; 27.1303; 27.1305(a),
(c) through (m), (r);
PCR.1305(b) A cylinder head temperature warning device to indicate
when the temperature exceeds a safe value.
27.1307; 27.1309(a) and (c); 27.1321(a) and (c); 27.1322; 27.1323(a)
and (b); 27.1325(a),(c), and (d); 27.1327; 27.1337; 27.1351; 27.1353;
27.1357; 27.1361(a) and (c); 27.1365; 27.1367; 27.1401; 27.1411;
27.1413; 27.1461; 27.1501; 27.1503; 27.1505; 27.1509; 27.1521; 27.1523;
27.1525; 27.1527; 27.1529; 27.1541; 27.1543; 27.1545; 27.1547; 27.1549;
27.1551; 27.1553; 27.1555; 27.1557(a), (b), and (d);
PCR.1557(c) Fuel and Oil Filler Openings Marking. The following
apply:
(1) Fuel filler openings must be marked at or near the filler cover
with--
(i) The word ``fuel';
(ii) For reciprocating engine powered rotorcraft, the minimum fuel
grade; and
(iii) For each two stroke engine without a separate oil system, the
fuel/oil mixture.
(2) Oil filler openings must be marked at or near the filler cover
with the word ``oil''.
27.1559; 27.1565; 27.1581; 27.1583; 27.1585; 27.1587; 27.1589; 33.5;
33.7 (a) and (b); 33.8; 33.15; 33.17(a),(b),(c), and (e);
PCR.33.19 Engine design and construction must minimize the
development of an unsafe condition of the engine between overhaul
periods.
33.21; 33.23; 33.25; 33.29(a); 33.31; 33.33; 33.35; 33.37; 33.39;
PCR.33.39(d) For engine lubrication depending upon oil premixed
with fuel in a declared fixed percentage, it must be demonstrated that
this mixture can assure appropriate engine lubrication, throughout the
range of conditions in which the rotorcraft is expected to operate, to
include reduced fuel consumption conditions.
33.41; 33.42;
PCR.33.43 Vibration test. Each engine must undergo a vibration
survey when installed in the airframe to show compliance with 27.907
and 33.33. The survey must be conducted throughout the expected
operating range of rotational speed and power of the engine. Each
accessory drive and mounting attachment must be loaded with the maximum
loads expected in service.
33.45; 33.47;
PCR.33.49 Endurance Test
(a) The engine must be subjected to an endurance test that includes
a total of 50 hours of operation and consists of the cycles specified
in (b) below.
(b) Each cycle consists of 120 minutes of run time and must be
conducted as follows:
(1) A start and idle period of 5 minutes.
(2) Increase to takeoff torque and maximum speed for takeoff torque
and maintain the takeoff condition for a period of 5 minutes.
(3) Decrease to idle and maintain the idle condition for 5 minutes.
(4) Increase to takeoff torque and maximum speed for takeoff torque
and maintain the takeoff condition for a period of 5 minutes.
(5) Decrease to idle and maintain the idle condition for 5 minutes.
(6) Increase to takeoff torque and maximum speed for takeoff torque
and maintain the takeoff condition for a period of 5 minutes.
(7) Decrease to idle and maintain the idle condition for 5 minutes.
(8) Increase to 75 percent of maximum continuous torque and maximum
speed for 75 percent of maximum continuous torque and maintain this
condition for a period of 15 minutes.
(9) Decrease to idle and maintain the idle condition for 5 minutes.
(10) Increase to maximum continuous torque and maximum speed for
maximum continuous torque and maintain this condition for a period of
60 minutes.
[[Page 49177]]
(11) Decrease to idle and maintain the idle condition for 5
minutes.
(12) Perform an engine shutdown.
(c) During or following the endurance test the fuel and oil
consumption must be determined.
33.51; 33.53; 33.55; 33.57
Noise requirements of FAR Part 36 Noise Standards Appendix J
amended by amendments 36-1 through the latest amendment in effect at
the time of Type Certification.
Issued in Fort Worth, Texas, on September 3, 1997.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-25010 Filed 9-18-97; 8:45 am]
BILLING CODE 4910-13-P
