The provisions of this section shall apply to all rotorcraft types certificated under this part irrespective of the date of application for type certificate.

(a) Unless otherwise established by the Administrator, the rotorcraft shall comply with the provisions of this part together with all amendments thereto effective on the date of application for type certificate, except that compliance with later effective amendments may be elected or required pursuant to paragraphs (c), (d), and (e) of this section.

(b) If the interval between the date of application for type certificate and the issuance of the corresponding type certificate exceeds five years, a new application for type certificate shall be required. At the option of the applicant, a new application may be filed prior to the expiration of the five-year period. In either instance the applicable regu

lations shall be those effective on the date of the new application in accordance with paragraph (a) of this section.

(c) During the interval between filing the application and the issuance of a type certificate, the applicant may elect to show compliance with any amendment of this part which becomes effective during that interval, in which case all other amendments found by the Administrator to be directly related shall be complied with.

(d) Except as otherwise provided by the Administrator pursuant to § 1.24 of this subchapter, a change to the type certificate (see § 7.13(b)) may be accomplished, at the option of the holder of the type certificate, either in accordance with the regulations incorporated by reference in the type certificate pursuant to § 7.13 (c), or in accordance with subsequent amendments to such regulations in effect on the date of application for approval of the change, subject to the following provisions:

(1) When the applicant elects to show compliance with an amendment to the regulations in effect on the date of application for approval of a change, he shall show compliance with all amendments which the Administrator finds are directly related to the particular amendment selected by the applicant.

(2) When the change consists of a new design or a substantially complete redesign of a component, equipment installation, or system installation of the rotorcraft, and the Administrator finds that the regulations incorporated by reference in the type certificate pursuant to § 7.13 (c) do not provide complete standards with respect to such change, he shall require compliance with such provisions of the regulations in effect on the date of application for approval of the change as he finds will provide a level of safety equal to that established by the regulations incorporated by reference at the time of issuance of the type certificate.

NOTE: Examples of new or redesigned components and installations which might require compliance with regulations in effect on the date of application for approval, are: New powerplant installation which is likely to introduce additional fire or operational hazards unless additional protective measures are incorporated; the installation of a new rotor system or a new electric power system.

(e) If changes listed in subparagraphs (1) through (3) of this paragraph are

made, the rotorcraft shall be considered as a new type, in which case a new application for type certificate shall be required and the regulations together with all amendments thereto effective on the date of the new application shall be made applicable in accordance with paragraphs (a), (b), (c), and (d) of this section.

(1) A change in the number of engines or rotors;

(2) A change to engines or rotors employing different principles of operation or propulsion;

(3) A change in design, configuration, power, or weight which the Administrator finds is so extensive as to require a substantially complete investigation of compliance with the regulations.

[21 F.R. 3744, June 2, 1956, as amended, 24 F.R. 5, Jan. 1, 1959]

§ 7.12 Recording of applicable regulations.

The Administrator, upon the issuance of a type certificate, shall record the applicable regulations with which compliance was demonstrated. Thereafter, the Administrator shall record the applicable regulations for each change in the type certificate which is accomplished in accordance with regulations other than those recorded at the time of issuance of the type certificate. (See § 7.11.)

§ 7.13 Type certificate.

(a) An applicant shall be issued a type certificate when he demonstrates the eligibility of the rotorcraft by complying with the requirements of this part in addition to the applicable requirements in Part I of this subchapter.

(b) The type certificate shall be deemed to include the type design (see § 7.14 (b)), the operating limitations for the rotorcraft (see § 7.700), and any other conditions or limitations prescribed by the regulations in this subchapter.

(c) The applicable provisions of this part recorded by the Administrator in accordance with § 7.12 shall be considered as incorporated in the type certifi.. cate as though set forth in full.

§ 7.14 Data required.

(a) The applicant for a type certificate shall submit to the Administrator such descriptive data, test reports, and computations as are necessary to demonstrate that the rotorcraft complies with the requirements of this part.

(b) The descriptive data required in paragraph (a) of this section shall be known as the type design and shall consist of such drawings and specifications as are necessary to disclose the configuration of the rotorcraft and all the design features covered in the requirements of this part, such information on dimensions, materials, and processes as is necessary to define the structural strength of the rotorcraft, and such other data as are necessary to permit by comparison the determination of the airworthiness of subsequent rotorcraft of the same type.

§ 7.15 Inspections and tests.

Inspections and tests shall include all those found necessary by the Administrator to insure that the rotorcraft complies with the applicable airworthiness requirements and conforms to the following:

(a) All materials and products are in accordance with the specifications in the type design,

(b) All parts of the rotorcraft are constructed in accordance with the drawings in the type design,

(c) All manufacturing processes, construction, and assembly are as specified in the type design.

§ 7.16 Flight tests.

After proof of compliance with the structural requirements contained in this part, and upon completion of all necessary inspections and testing on the ground, and proof of the conformity of the rotorcraft with the type design, and upon receipt from the applicant of a report of flight tests performed by him, the following shall be conducted:

(a) Such official flight tests as the Administrator finds necessary to determine compliance with the requirements of this part.

(b) After the conclusion of flight tests specified in paragraph (a) of this section, such additional flight tests as the Administrator finds necessary to ascertain whether there is reasonable assurance that the rotorcraft, its components, and equipment are reliable and function properly. The extent of such additional flight tests shall depend upon the complexity of the rotorcraft, the number and nature of new design features, and the record of previous tests and experience for the particular rotorcraft type, its components, and equip

ment. If practicable, these flight tests shall be conducted on the same rotorcraft used in the flight tests specified in paragraph (a) of this section and in the rotor drive endurance tests specified in § 7.405. § 7.17

Airworthiness, experimental, and production certificates.

(For requirements with regard to these certificates see Part 1 of this subchapter.)

§ 7.18 Approval of materials, parts, processes, and appliances.

(a) Materials, parts, processes, and appliances shall be approved upon a basis and in a manner found necessary by the Administrator to implement the pertinent provisions of the regulations in this subchapter. The Administrator may adopt and publish such specifications as he finds necessary to administer this regulation, and shall incorporate therein such portions of the aviation industry, Federal, and military specifications respecting such materials, parts, processes, and appliances as he finds appropriate.

NOTE: The provisions of this paragraph are intended to allow approval of materials, parts, processes, and appliances under the system of Technical Standard Orders, or in conjunction with type certification procedures for a rotocraft, or by any other form of approval by the Administrator.

(b) Any material, part, process, or appliance shall be deemed to have met the requirements for approval when it meets the pertinent specifications adopted by the Administrator, and the manufacturer so certifies in a manner prescribed by the Administrator.

§ 7.19 Changes in type design.

(For requirements with regard to changes in type design and the designation of applicable regulations therefor, see § 7.11 (d) or (e), and Part 1 of this subchapter.)

to 20,000 pounds or less, and can be single- or multiengined.

(b) A multiengined rotorcraft may be certificated under the requirements of a particular category, or in both categories, if all of the requirements of each category are met. Sections of this part which apply to only one category are identified by the appropriate suffix added to the section number, as indicated in paragraph (a) of this section. All sections not identified by a suffix are applicable to both categories except as otherwise specified.

Subpart B-Flight

GENERAL

§ 7.100 Proof of compliance.

(a) Compliance with the requirements prescribed in this subpart shall be established by flight or other tests conducted upon a rotorcraft of the type for which a certificate of airworthiness is sought or by calculations based on such tests, provided that the results obtained by calculations are equivalent in accuracy to the results of direct testing.

(b) Compliance with each requirement shall be established at all appropriate combinations of rotorcraft weight and center of gravity position within the range of loading conditions for which certification is sought by systematic investigation of all these combinations, except where compliance can be inferred reasonably from those combinations which are investigated.

(c) The controllability, stability, and trim of the rotorcraft shall be established at all altitudes up to the maximum anticipated operating altitude.

(d) The applicant shall provide a person holding an appropriate pilot certificate to make the flight tests, but a designated representative of the Administrator shall pilot the rotorcraft when it is found necessary for the determination of compliance with the airworthiness requirements.

(e) Official type tests shall be discontinued until corrective measures have been taken by the applicant when either:

(1) The applicant's test pilot is unable or unwilling to conduct any of the required flight tests, or

(2) It is found that requirements which have not been met are so substantial as to render additional test data

(f) Adequate provision shall be made for emergency egress and for the use of parachutes by members of the crew during the flight tests.

(g) The applicant shall submit to the authorized representative of the Administrator a report covering all computations and tests required in connection with calibration of instruments used for test purposes and correction of test results to standard atmospheric conditions. The authorized representative of the Administrator shall conduct any flight tests which he finds necessary to check the calibration and correction report.

§ 7.101 Weight limitations.

The maximum and minimum weights at which the rotorcraft will be suitable for operation shall be established as follows:

(a) Maximum weights shall not exceed any of the following:

(1) The weight selected by the applicant;

(2) The design weight for which the structure has been proven; or

(3) The maximum weight at which compliance with all the applicable flight requirements has been demonstrated.

(b) It shall be acceptable to establish maximum weights for each altitude and for each practicably separable operating condition; e. g., take-off, en route, landing.

(c) Minimum weights shall not be less than any of the following:

(1) The minimum weight selected by the applicant;

(2) The design minimum weight for which the structure has been proven; or

(3) The minimum weight at which compliance with all of the applicable flight requirements has been demonstrated. (See § 7.741 (c).)

(1) The extremes selected by the applicant,

(2) The extremes for which the structure has been proven,

(3) The extremes at which compliance with all of the applicable flight requirements has been demonstrated.

(b) Loading instructions shall be provided if the center of gravity position under any possible loading condition between the maximum and minimum weights as specified in § 7.101, with assumed weights for individual passengers and crew members variable over the anticipated range of such weights, lies beyond:

(1) The extremes selected by the applicant,

(2) The extremes for which the structure has been proven,

(3) The extremes for which compliance with all of the applicable flight requirements has been demonstrated. (See § 7.741 (c).)

§ 7.103 Rotor limitations and pitch settings.

(a) Power-on. A range of power-on operating speeds for the main rotor(s) shall be established which will provide adequate margin to accommodate the variation of rotor rpm attendant to all maneuvers appropriate to the rotorcraft type and consistent with the type of synchronizer or governor used, if any (see §§ 7.713(b) (2) and 7.714(b)), however, such means need not be provided if the Administrator finds that inherent characteristics of the rotorcraft render it unnecessary or that adequate means of warning the pilot of unsafe rotor speeds are provided. If a means to prevent low rotor speeds is provided, a means shall be provided to prevent rotational speeds substantially less than the approved minimum rotor rpm in any sustained flight condition with full throttle and with pitch control of the main rotor(s) in the high-pitch position. It shall be acceptable for such means to allow the use of higher pitch in an emergency, provided that the means incorporate provisions to prevent inadvertent transition from the normal operating range to the higher pitch angles.

(b) Power-off. A range of power-off operating rotor speeds shall be established which will permit execution of all autorotative flight maneuvers appropriate to the rotorcraft type throughout

the range of air speeds and weights for which certification is sought (see §§ 7.713 (a) and 7.713 (b) (1)). A rotor blade low-pitch limiting device shall be positioned to provide sufficient rotational speed within the approved rotor speed range in any autorotative flight condition under the most adverse combinations of weight and air speed with the rotor pitch control in the full low-pitch position. However, it shall be possible to prevent overspeeding of the rotor without requiring exceptional piloting skill.

[21 F.R. 3744, June 2, 1956, as amended by Amdt. 7-2, 23 F.R. 2593, Apr. 19, 1958; Amdt. 7-3, 23 F.R. 3514, May 22, 1958]

§ 7.104 Empty weight.

(a) The empty weight, and the corresponding center of gravity position, shall be determined by weighing the rotorcraft. This weight shall exclude the weight of the crew and payload, but shall include the weight of all fixed ballast, unusable fuel supply (see § 7.416), undrainable oil, total quantity of engine coolant, and total quantity of hydraulic fluid.

(b) The condition of the rotorcraft at the time of weighing shall be one which can be easily repeated and easily defined, particularly as regards the contents of the fuel, oil, and coolant tanks, and the items of equipment installed. (See § 7.740.)

§ 7.105 Use of ballast.

Removable ballast may be used to enable the rotorcraft to comply with the flight requirements. (See §§ 7.391, 7.738, and 7.740.)

(a) The performance prescribed in this subpart shall be determined using normal pilot skill and shall not require exceptionally favorable conditions. Compliance shall be shown for sea level standard conditions in still air and for the range of atmospheric variables as selected by the applicant. The performance as affected by engine power, instead of being based on dry air, shall be based on 80 percent relative humidity or 0.7" Hg. vapor pressure, whichever is less.

(b) Each set of performance data required for a particular flight condition shall be determined with the powerplant accessories absorbing the normal amount

of power appropriate to that flight condition.

NOTE: The Administrator is authorized to establish appropriate margins to be applied to the performance data determined in accordance with this part for operating variables not covered in the performance determination; e. g., variations in pilot technique, engine power, rotor drag, rough air, etc. § 7.111 Limiting height and speeds for safe landing following power failure. (a) Category A. If a range of heights exists at any speed, including zero, within which it is not possible to make a safe landing when the critical engine is suddenly made inoperative with take-off power on the operating engine (s), the range of heights and its variation with forward speed shall be established (see §§ 7.715 and 7.741 (f)).

(b) Category B. If a range of heights exists at any speed, including zero, within which it is not possible to make a safe landing following complete power failure, the range of heights and its variation with forward speed shall be established (see §§ 7.715 and 7.741 (f)).

(c) Category B; optional requirements for multiengined rotorcraft. In lieu of compliance with paragraph (b) of this section, a multiengine rotorcraft that is certificated in accordance with Transport Category A powerplant installation requirements may, at the option of the applicant, comply with paragraph (a) of this section.

NOTE: (See § 7.384 (b).) Category B rotorcraft structure, controls, rotor mechanisms, and parts essential to a controlled landing are protected from powerplant fires for at least 5 minutes.

[21 F.R. 3744, June 2, 1956, as amended by Amdt. 7-2, 23 F.R. 2593, Apr. 19, 1958]

§ 7.112 Take-off; general.

(a) Category A: The take-off performance shall be determined and scheduled in such a manner that, in the event of one engine becoming inoperative at any instant after the start of take-off, it shall be possible for the rotorcraft either to return to and stop safely on the take-off area, or to continue the take-off, climbout, and attain a rotorcraft configuration and airspeed at which compliance with the climb requirement of § 7.115 (a) (2) is met.

(b) The take-off data required by §§ 7.113, 7.114, and 7.115 (a) (1) and (2)