[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