[Code of Federal Regulations]

[Title 14, Volume 1]

[Revised as of January 1, 2006]

From the U.S. Government Printing Office via GPO Access

[CITE: 14CFR27.25]



[Page 569-570]

 

                     TITLE 14--AERONAUTICS AND SPACE

 

CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION

 

PART 27_AIRWORTHINESS STANDARDS: NORMAL CATEGORY ROTORCRAFT--Table 

of Contents

 

                            Subpart B_Flight

 

Sec. 27.25  Weight limits.



    (a) Maximum weight. The maximum weight (the highest weight at which 

compliance with each applicable requirement of this part is shown) must 

be established so that it is--

    (1) Not more than--

    (i) The highest weight selected by the applicant;

    (ii) The design maximum (the highest weight at which compliance with 

each applicable structural loading condition of this part is shown); or

    (iii) The highest weight at which compliance with each applicable 

flight requirement of this part is shown; and

    (2) Not less than the sum of--

    (i) The empty weight determined under Sec. 27.29; and

    (ii) The weight of usable fuel appropriate to the intended operation 

with full payload;

    (iii) The weight of full oil capacity; and



[[Page 570]]



    (iv) For each seat, an occupant weight of 170 pounds or any lower 

weight for which certification is requested.

    (b) Minimum weight. The minimum weight (the lowest weight at which 

compliance with each applicable requirement of this part is shown) must 

be established so that it is--

    (1) Not more than the sum of--

    (i) The empty weight determined under Sec. 27.29; and

    (ii) The weight of the minimum crew necessary to operate the 

rotorcraft, assuming for each crewmember a weight no more than 170 

pounds, or any lower weight selected by the applicant or included in the 

loading instructions; and

    (2) Not less than--

    (i) The lowest weight selected by the applicant;

    (ii) The design minimum weight (the lowest weight at which 

compliance with each applicable structural loading condition of this 

part is shown); or

    (iii) The lowest weight at which compliance with each applicable 

flight requirement of this part is shown.

    (c) Total weight with jettisonable external load. A total weight for 

the rotorcraft with a jettisonable external load attached that is 

greater than the maximum weight established under paragraph (a) of this 

section may be established for any rotorcraft-load combination if--

    (1) The rotorcraft-load combination does not include human external 

cargo,

    (2) Structural component approval for external load operations under 

either Sec. 27.865 or under equivalent operational standards is 

obtained,

    (3) The portion of the total weight that is greater than the maximum 

weight established under paragraph (a) of this section is made up only 

of the weight of all or part of the jettisonable external load,

    (4) Structural components of the rotorcraft are shown to comply with 

the applicable structural requirements of this part under the increased 

loads and stresses caused by the weight increase over that established 

under paragraph (a) of this section, and

    (5) Operation of the rotorcraft at a total weight greater than the 

maximum certificated weight established under paragraph (a) of this 

section is limited by appropriate operating limitations under Sec. 

27.865(a) and (d) of this part.



(Secs. 313(a), 601, 603, 604, and 605 of the Federal Aviation Act of 

1958 (49 U.S.C. 1354(a), 1421, 1423, 1424, and 1425); and sec. 6(c) of 

the Dept. of Transportation Act (49 U.S.C. 1655(c)))



[Doc. No. 5074, 29 FR 15695, Nov. 29, 1964, as amended by Amdt. 27-11, 

41 FR 55468, Dec. 20, 1976; Amdt. 25-42, 43 FR 2324, Jan. 16, 1978; 

Amdt. 27-36, 64 FR 43019, Aug. 6, 1999]