385 

Federal Aviation Administration, DOT 

§ 129.24 

radio communication equipment nec-
essary under normal operating condi-
tions to fulfill the following: 

(1) Communicate with at least one 

appropriate station from any point on 
the route; 

(2) Communicate with appropriate air 

traffic control facilities from any point 
within Class B, Class C, or Class D air-
space, or within a Class E surface area 
designated for an airport in which 
flights are intended; and 

(3) Receive meteorological informa-

tion from any point en route. 

(b) No foreign air carrier may operate 

a rotorcraft at night under VFR over 
routes that can be navigated by pilot-
age unless that rotorcraft is equipped 
with— 

(1) Radio communication equipment 

necessary under normal operating con-
ditions to fulfill the functions specified 
in paragraph (a) of this section; and 

(2) Navigation equipment suitable for 

the route to be flown. 

[Doc. No. FAA–2002–14002, 72 FR 31683, June 7, 
2007] 

§ 129.23

Transport category cargo 

service airplanes: Increased zero 
fuel and landing weights. 

(a) Notwithstanding the applicable 

structural provisions of the transport 
category airworthiness regulations, 
but subject to paragraphs (b) through 
(g) of this section, a foreign air carrier 
may operate (for cargo service only) 
any of the following transport category 
airplanes (certificated under part 4b of 
the Civil Air Regulations effective be-
fore March 13, 1956) at increased zero 
fuel and landing weights— 

(1) DC–6A, DC–6B, DC–7B, and DC–7C; 

and 

(2) L–1049 B, C, D, E, F, G, and H, and 

the L–1649A when modified in accord-
ance with supplemental type certifi-
cate SA 4–1402. 

(b) The zero fuel weight (maximum 

weight of the airplane with no dispos-
able fuel and oil) and the structural 
landing weight may be increased be-
yond the maximum approved in full 
compliance with applicable rules only 
if the Administrator finds that— 

(1) The increase is not likely to re-

duce seriously the structural strength; 

(2) The probability of sudden fatigue 

failure is not noticeably increased; 

(3) The flutter, deformation, and vi-

bration characteristics do not fall 
below those required by applicable reg-
ulations; and 

(4) All other applicable weight limi-

tations will be met. 

(c) No zero fuel weight may be in-

creased by more than five percent, and 
the increase in the structural landing 
weight may not exceed the amount, in 
pounds, of the increase in zero fuel 
weight. 

(d) Each airplane must be inspected 

in accordance with the approved spe-
cial inspection procedures, for oper-
ations at increased weights, estab-
lished and issued by the manufacturer 
of the type of airplane. 

(e) A foreign air carrier may not op-

erate an airplane under this section un-
less the country of registry requires 
the airplane to be operated in accord-
ance with the passenger-carrying 
transport category performance oper-
ating limitations in part 121 or the 
equivalent. 

(f) The Airplane Flight Manual for 

each airplane operated under this sec-
tion must be appropriately revised to 
include the operating limitations and 
information needed for operation at 
the increased weights. 

(g) Each airplane operated at an in-

creased weight under this section 
must, before it is used in passenger 
service, be inspected under the special 
inspection procedures for return to pas-
senger service established and issued 
by the manufacturer and approved by 
the Administrator. 

[Doc. No. 6403, 29 FR 19098, Dec. 30, 1964] 

§ 129.24

Cockpit voice recorders. 

No person may operate an aircraft 

under this part that is registered in the 
United States unless it is equipped 
with an approved cockpit voice re-
corder that meets the standards of 
TSO–C123a, or later revision. The cock-
pit voice recorder must record the in-
formation that would be required to be 
recorded if the aircraft were operated 
under part 121, 125, or 135 of this chap-
ter, and must be installed by the com-
pliance times required by that part, as 
applicable to the aircraft. 

[Doc. No. FAA–2005–20245, 73 FR 12570, Mar. 7, 
2008] 

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