[Federal Register Volume 63, Number 63 (Thursday, April 2, 1998)]
[Rules and Regulations]
[Pages 16089-16091]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-7411]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 21
Airworthiness Standards for Acceptance Under the Primary Category
Rule
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final Airworthiness Standards for Acceptance of the Dragonfly
Model 333 Helicopter Under the Primary Category Rule.
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SUMMARY: This document announces the approval of final airworthiness
standards for acceptance of the Dragonfly Model 333 helicopter under
the primary category rule. The final airworthiness standards are
provided in this document.
DATES: This final airworthiness standard is effective March 10, 1998.
FOR FURTHER INFORMATION CONTACT: Scott Horn, Aerospace Engineer,
Rotorcraft Standards Staff, Rotorcraft Directorate, Aircraft
Certification Service, Federal Aviation Administration, Fort Worth,
Texas 76193-0110; telephone number (817) 222-5125, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: Any person may obtain a copy of this
information by contacting the person named above under FOR FURTHER
INFORMATION CONTACT.
[[Page 16090]]
Background
The primary category rule was created specifically for the simple,
low performance personal aircraft. Potential applicants are permitted
to propose airworthiness standards considered appropriate for the
intended product. Accordingly, the applicant, Dragon Fly, submitted a
request to include the Italian airworthiness authority's Very Light
Rotorcraft (VLR) rules into primary category for rotorcraft.
Dragon Fly justifies this request by noting that the Italian
airworthiness authority has approved the applicant's aircraft in Italy
under the VLR rules. The FAA reviewed the submittal and chose to list
the Italian VLR rules as the equivalent 14 CFR parts 27 and 33 (parts
27 and 33) rules and, in some cases, added paragraphs to increase the
requirement.
The FAA issued the proposed airworthiness standards; request for
comments, on September 3, 1997 (62 FR 49175, September 19, 1997). One
comment was received. The commenter concurs with the proposed
airworthiness standards. However, the commenter states that additional
airworthiness requirements are needed to require the manufacturer to
provide data on the response of the helicopter to flight control inputs
and to require operational limitations or other measures for those
aircraft that are highly responsive. The FAA does not agree that
additional requirements are needed. The response of the rotor and
helicopter to various flight control inputs will be fully investigated
under the current requirements. To investigate the need for operational
limitations, the FAA requires a Flight Standardization Board on all
light helicopters. Primary category helicopters are included in this
requirement.
Additionally, after the publication of the proposed airworthiness
standards, the FAA met with Dragon Fly to discuss the certification.
The applicant provided further details of their design which affect the
airworthiness standards to be listed in the certification basis.
Section 27.2 is not required since the safety belt and shoulder harness
requirements will be addressed in Sec. 27.785. Sections 27.65(b)
determination of Vy, 27.141(c) requirements for night operation, 27.303
a safety factor of 1.5 for loads, 27.775 windshield and window
requirements, and 27.1519 weight and center of gravity limitation
requirements will be added. A wind velocity of 17 knots from all
azimuths will be added to PCR.143(c) making it equivalent to 27.143(c).
Paragraph 27.143(c) will replace PCR.143(c). The helicopter will not be
configured with wheels, tires, brakes, floats, cargo or baggage
compartments, skis, or shock absorbers. Therefore, Secs. 27.475,
27.477, 27.479, 27.481, 27.483, 27.485, 27.493, 27.497, 27.505, 27.521,
27.731, 27.733, 27.735, 27.737, 27.751, 27.753, 27.755, and 27.787 will
be removed. The applicant also requested VFR night operation.
Therefore, Secs. 27.1381, 27.1383, 27.1385, 27.1387, 27.1389, 27.1391,
27.1393, 27.1395, 27.1397, and 27.1399, will be added. Section
27.923(l), as published in the ``Request for Comments'' (62 FR 49175,
September 19, 1997), should have read 27.923(i). Section 27.923(h) has
been added because paragraph (h) was part of the original Dragon Fly
Registro Aeronautico Italiano (RAI) VLR certification.
The authority citation for these airworthiness standards is as
follows:
42 U.S.C. 7572; 49 U.S.C. 106(g), 40105, 40113, 44701-44702, 44707,
44708, 44711, 44713, 44715, 45303.
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. 27.21;
27.25(a) and (b); 27.27; 27.29; 27.31; 27.33; 27.45(a), (b), (c), and
(d); 27.51; 27.65(b); 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), (b)(3) and (c); 27.143(a), (b), (c), (d), and (e);
27.151; 27.161; 27.171; 27.173; 27.175; 27.177; 27.231; 27.235; 27.239;
27.241; 27.251; 27.301; 27.303; 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; 27.501; 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 are 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 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; 27.771; 27.773; 27.775; 27.777; 27.779; 27.783;
27.785 (a), (b), (c), (e), (f), (g), (h), (i), and (j); 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),
(h) and (i); 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
[[Page 16091]]
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). Paragraph (r) is
deleted from this Notice. It was inadvertently included in the request
for comments but applies to turbine installations only. 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; 27.1381; 27.1383; 27.1385; 27.1387, 27.1389; 27.1391;
27.1393; 27.1395; 27.1397; 27.1399; 27.1401; 27.1411; 27.1413; 27.1461;
27.1501; 27.1503; 27.1505; 27.1509; 27.1519; 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.
(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 March 10, 1998.
Eric Bries,
Assistant Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 98-7411 Filed 4-1-98; 8:45 am]
BILLING CODE 4910-13-P
