[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