Text in force at CS29-12: from CS29-1, effective 30 Nov 2007.
(a) Maximum weight. T he ma ximum weight (the highest weight at which compliance with each applicable requirement of this CS–29 is shown) or, at t he opt ion of t he appl icant, t he highest weight for each altitude and for each practicably separable operating condi tion, such as t ake-off, en-route operation, and l anding, m ust be established so that it is not more than:
(1) The highest weight sel ected by t he applicant;
(2) The desi gn m aximum weight (the highest weight at which com pliance with each applicable structural loading condi tion of t his CS–29 is shown); or
(3) The hi ghest wei ght at whi ch compliance with each applicable flight requirement of this CS–29 is shown.
(4) For Category B rotorcraft with 9 or less passenger seat s, t he maximum weight, altitude, and temperature at which the rotorcraft can safely operate near t he ground wi th t he maximum wind velocity det ermined under C S 29.143(c) and m ay i nclude other demonstrated wind v elocities an d azim uths. Th e o perating envelopes m ust be st ated in the Limitations section of the Rotorcraft Flight Manual.
(b) Minimum weight. T he mi nimum weight (the lowest weight at which com pliance with each applicable requirement of t his C S–29 i s shown) must be established so that it is not less than:
(1) The lowest weight selected by the applicant;
(2) The desi gn m inimum weight (the lowest weight at which com pliance with each structural loading condition of t his C S–29 i s shown); or
(3) The lowest weight at which compliance with each applicable flight requirement of this CS–29 is shown.
(c) Total weight with jettisonable external load. A total weight for the rotorcraft with a jettisonable ex ternal lo ad attach ed th at is greater than t he m aximum wei ght est ablished under sub-paragraph (a) may be est ablished for any rotorcraft-load combination if:
(1) The rotorcraft-load combination does not include human external cargo, (2) Structural component approval for external load operat ions under ei ther C S 29.865, or under equi valent operat ional standards is obtained, (3) The p ortion o f th e total weight that is greater than the maximum weight established under sub-paragraph (a) i s made up onl y of the weight of all o r part of the jettisonable external load, (4) Structural com ponents of t he rotorcraft are sh own to co mply with the applicable structural requirements of this CS-29 under t he i ncreased l oads and stresses caused by the weight increase over that established under sub-paragraph (a), and (5) Operation of the rotorcraft at a total weight greater than th e m aximum certificated weight est ablished under sub-paragraph (a) i s limited b y ap propriate operating limitations under CS 29.865(a) and (d).
ED Decision 2007/014/R · Source