Section 29.75

14 CFR Ch. I (1-1-19 Edition)

of category A, the steady angle of glide
must be determined in autorotation - 
(a) At the forward speed for minimum rate of descent as selected by the
applicant;
(b) At the forward speed for best glide
angle;
(c) At maximum weight; and
(d) At the rotor speed or speeds selected by the applicant.
[Amdt. 29-12, 41 FR 55471, Dec. 20, 1976]

Section 29.75

Landing: General.

(a) For each rotorcraft - 
(1) The corrected landing data must
be determined for a smooth, dry, hard,
and level surface;
(2) The approach and landing must
not require exceptional piloting skill
or exceptionally favorable conditions;
and
(3) The landing must be made without excessive vertical acceleration or
tendency to bounce, nose over, ground
loop, porpoise, or water loop.
(b) The landing data required by
SectionSection 29.77, 29.79, 29.81, 29.83, and 29.85 must
be determined - 
(1) At each weight, altitude, and temperature for which landing data are approved;
(2) With each operating engine within
approved operating limitations; and
(3) With the most unfavorable center
of gravity.
[Doc. No. 24802, 61 FR 21900, May 10, 1996]

Section 29.77 Landing Decision Point (LDP):
Category A.
(a) The LDP is the last point in the
approach and landing path from which
a balked landing can be accomplished
in accordance with Section 29.85.
(b) Determination of the LDP must
include the pilot recognition time interval following failure of the critical
engine.
[Doc. No. 24802, 64 FR 45338, Aug. 19, 1999]

spaschal on DSK3GDR082PROD with CFR

Section 29.79

Landing: Category A.

(a) For Category A rotorcraft - 
(1) The landing performance must be
determined and scheduled so that if the
critical engine fails at any point in the
approach path, the rotorcraft can either land and stop safely or climb out
and attain a rotorcraft configuration

and speed allowing compliance with
the climb requirement of Section 29.67(a)(2);
(2) The approach and landing paths
must be established with the critical
engine inoperative so that the transition between each stage can be made
smoothly and safely;
(3) The approach and landing speeds
must be selected by the applicant and
must be appropriate to the type of
rotorcraft; and
(4) The approach and landing path
must be established to avoid the critical areas of the height-velocity envelope determined in accordance with
Section 29.87.
(b) It must be possible to make a safe
landing on a prepared landing surface
after complete power failure occurring
during normal cruise.
[Doc. No. 24802, 61 FR 21900, May 10, 1996]

Section 29.81

Landing distance: Category A.

The horizontal distance required to
land and come to a complete stop (or to
a speed of approximately 3 knots for
water landings) from a point 50 ft
above the landing surface must be determined from the approach and landing paths established in accordance
with Section 29.79.
[Doc. No. 24802, 64 FR 45338, Aug. 19, 1999]

Section 29.83

Landing: Category B.

(a) For each Category B rotorcraft,
the horizontal distance required to
land and come to a complete stop (or to
a speed of approximately 3 knots for
water landings) from a point 50 feet
above the landing surface must be determined with - 
(1) Speeds appropriate to the type of
rotorcraft and chosen by the applicant
to avoid the critical areas of the
height-velocity envelope established
under Section 29.87; and
(2) The approach and landing made
with power on and within approved
limits.
(b) Each multiengined Category B
rotorcraft that meets the powerplant
installation requirements for Category
A must meet the requirements of - 
(1) Sections 29.79 and 29.81; or
(2) Paragraph (a) of this section.
(c) It must be possible to make a safe
landing on a prepared landing surface if

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