[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: 14CFR29.25]



[Page 650-651]

 

                     TITLE 14--AERONAUTICS AND SPACE

 

CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION

 

PART 29_AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY ROTORCRAFT--Table 

of Contents

 

                            Subpart B_Flight

 

Sec. 29.25  Weight limits.



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

compliance with each applicable requirement of this part is shown) or, 

at the option of the applicant, the highest weight for each altitude and 

for each practicably separable operating condition, such as takeoff, 

enroute operation, and landing, must be established so that it is not 

more than--

    (1) The highest weight selected by the applicant;

    (2) The design maximum weight (the highest weight at which 

compliance with each applicable structural loading condition of this 

part is shown); or

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

flight requirement of this part is shown.

    (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 not less than--

    (1) The lowest weight selected by the applicant;

    (2) The design minimum weight (the lowest weight at which compliance 

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

    (3) 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. 29.865 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



[[Page 651]]



    (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. 

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



[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as amended by Amdt. 29-12, 41 

FR 55471, Dec. 20, 1976; Amdt. 29-43, 64 FR 43020, Aug. 6, 1999]