490 

14 CFR Ch. I (1–1–24 Edition) 

§ 27.21 

equipped with a safety belt and shoul-
der harness that meets the require-
ments of paragraphs (a), (b), and (c) of 
this section. 

(1) Each occupant’s seat must have a 

combined safety belt and shoulder har-
ness with a single-point release. Each 
pilot’s combined safety belt and shoul-
der harness must allow each pilot, 
when seated with safety belt and shoul-
der harness fastened, to perform all 
functions necessary for flight oper-
ations. There must be a means to se-
cure belts and harnesses, when not in 
use, to prevent interference with the 
operation of the rotorcraft and with 
rapid egress in an emergency. 

(2) Each occupant must be protected 

from serious head injury by a safety 
belt plus a shoulder harness that will 
prevent the head from contacting any 
injurious object. 

(3) The safety belt and shoulder har-

ness must meet the static and dynamic 
strength requirements, if applicable, 
specified by the rotorcraft type certifi-
cation basis. 

(4) For purposes of this section, the 

date of manufacture is either— 

(i) The date the inspection accept-

ance records, or equivalent, reflect 
that the rotorcraft is complete and 
meets the FAA-Approved Type Design 
Data; or 

(ii) The date the foreign civil air-

worthiness authority certifies that the 
rotorcraft is complete and issues an 
original standard airworthiness certifi-
cate, or equivalent, in that country. 

(b) For rotorcraft with a certification 

basis established prior to October 18, 
1999— 

(1) The maximum passenger seat ca-

pacity may be increased to eight or 
nine provided the applicant shows com-
pliance with all the airworthiness re-
quirements of this part in effect on Oc-
tober 18, 1999. 

(2) The maximum weight may be in-

creased to greater than 6,000 pounds 
provided— 

(i) The number of passenger seats is 

not increased above the maximum 
number certificated on October 18, 1999, 
or 

(ii) The applicant shows compliance 

with all of the airworthiness require-

ments of this part in effect on October 
18, 1999. 

[Doc. No. 26078, 56 FR 41051, Aug. 16, 1991, as 
amended by Amdt. 27–37, 64 FR 45094, Aug. 18, 
1999] 

Subpart B—Flight 

G

ENERAL

 

§ 27.21

Proof of compliance. 

Each requirement of this subpart 

must be met at each appropriate com-
bination of weight and center of grav-
ity within the range of loading condi-
tions for which certification is re-
quested. This must be shown— 

(a) By tests upon a rotorcraft of the 

type for which certification is re-
quested, or by calculations based on, 
and equal in accuracy to, the results of 
testing; and 

(b) By systematic investigation of 

each required combination of weight 
and center of gravity if compliance 
cannot be reasonably inferred from 
combinations investigated. 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–21, 49 FR 44432, Nov. 6, 
1984] 

§ 27.25

Weight limits. 

(a) 

Maximum weight. The maximum 

weight (the highest weight at which 
compliance with each applicable re-
quirement 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 weight (the 

highest weight at which compliance 
with each applicable structural loading 
condition of this part is shown); 

(iii) The highest weight at which 

compliance with each applicable flight 
requirement of this part is shown; or 

(iv) The highest weight in which the 

provisions of §§ 27.87 or 27.143(c)(1), or 
combinations thereof, are dem-
onstrated if the weights and operating 
conditions (altitude and temperature) 
prescribed by those requirements can-
not be met; and 

(2) Not less than the sum of— 
(i) The empty weight determined 

under § 27.29; and 

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