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Appendix C to Part 121 - C-46 Nontransport Category Airplanes
Cargo Operations
1. Required engines. (a) Except as provided in paragraph (b) of
this section, the engines specified in subparagraphs (1) or (2) of this
section must be installed in C-46 nontransport category airplanes operated
at gross weights exceeding 45,000 pounds:
(1) Pratt and Whitney R2800-51-M1 or R2800-75-M1 engines (engines
converted from basic model R2800-51 or R2800-75 engines in accordance with
FAA approved data) that --
(i) Conform to Engine Specification 5E-8;
(ii) Conform to the applicable portions of the operator's manual;
(iii) Comply with all the applicable airworthiness directives; and
(iv) Are equipped with high capacity oil pump drive gears in accordance
with FAA approved data.
(2) Other engines found acceptable by the FAA Regional Flight Standards
Division having type certification responsibility for the C-46 airplane.
(b) Upon application by an operator conducting cargo operations with
nontransport category C-46 airplanes between points within the State of
Alaska, the appropriate FAA Flight Standards District Office, Alaskan
Region, may authorize the operation of such airplanes, between points
within the State of Alaska; without compliance with paragraph (a) of this
section if the operator shows that, in its area of operation, installation
of the modified engines is not necessary to provide adequate cooling for
single-engine operations. Such authorization and any conditions or
limitations therefor is made a part of the Operations Specifications of
the operator.
2. Minimum acceptable means of complying with the special
airworthiness requirements. Unless otherwise authorized under
§121.213, the data set forth in sections 3 through 34 of this appendix, as
correlated to the C-46 nontransport category airplane, is the minimum
means of compliance with the special airworthiness requirements of
§§121.215 through 121.281.
3. Susceptibility of material to fire. [Deleted as unnecessary]
4. Cabin interiors. C-46 crew compartments must meet all the
requirements of §121.215, and, as required in §121.221, the door between
the crew compartment and main cabin (cargo) compartment must be flame
resistant.
5. Internal doors. Internal doors, including the crew to main
cabin door, must meet all the requirements of §121.217.
6. Ventilation. Standard C-46 crew compartments meet the
ventilation requirements of §121.219 if a means of ventilation for
controlling the flow of air is available between the crew compartment and
main cabin. The ventilation requirement may be met by use of a door
between the crew compartment and main cabin. The door need not have
louvers installed; however, if louvers are installed, they must be
controllable.
7. Fire precautions. Compliance is required with all the
provisions of §121.221.
(a) In establishing compliance with this section, the C-46 main cabin
is considered as a Class A compartment if --
(1) The operator utilizes a standard system of cargo loading and
tiedown that allows easy access in flight to all cargo in such
compartment, and, such system is included in the appropriate portion of
the operator's manual; and
(2) A cargo barrier is installed in the forward end of the main cabin
cargo compartment. The barrier must --
(i) Establish the most forward location beyond which cargo cannot be
carried;
(ii) Protect the components and systems of the airplane that are
essential to its safe operation from cargo damage; and
(iii) Permit easy access, in flight, to cargo in the main cabin cargo
compartment.
The barrier may be a cargo net or a network of steel cables or other
means acceptable to the Administrator which would provide equivalent
protection to that of a cargo net. The barrier need not meet crash load
requirements of FAR §25.561; however, it must be attached to the cargo
retention fittings and provide the degree of cargo retention that is
required by the operators' standard system of cargo loading and tiedown.
(b) C-46 forward and aft baggage compartments must meet, as a minimum,
Class B requirements of this section or be placarded in a manner to
preclude their use as cargo or baggage compartments.
8. Proof of compliance. The demonstration of compliance required
by §121.223 is not required for C-46 airplanes in which --
(1) The main cabin conforms to Class A cargo compartment requirements
of §121.219; and
(2) Forward and aft baggage compartments conform to Class B
requirements of §121.221, or are placarded to preclude their use as cargo
or baggage compartments.
9. Propeller deicing fluid. No change from the requirements of
§121.225. Isopropyl alcohol is a combustible fluid within the meaning of
this section.
10. Pressure cross-feed arrangements, location of fuel tanks, and
fuel system lines and fittings. C-46 fuel systems which conform to all
applicable Curtiss design specifications and which comply with the FAA
type certification requirements are in compliance with the provisions of
§§121.227 through 121.231.
11. Fuel lines and fittings in designated fire zones. No change
from the requirements of §121.233.
12. Fuel valves. Compliance is required with all the provisions
of §121.235. Compliance can be established by showing that the fuel system
conforms to all the applicable Curtiss design specifications, the FAA type
certification requirements, and, in addition, has explosion-proof fuel
booster pump electrical selector switches installed in lieu of the open
contact type used originally.
13. Oil lines and fittings in designated fire zones. No change
from the requirements of §121.237.
14. Oil valves. C-46 oil shutoff valves must conform to the
requirements of §121.239. In addition, C-46 airplanes using Hamilton
Standard propellers must provide, by use of stand pipes in the engine oil
tanks or other approved means, a positive source of oil for feathering
each propeller.
15. Oil system drains. The standard C-46 "Y" drains installed in
the main oil inlet line for each engine meet the requirements of §121.241.
16. Engine breather line. The standard C-46 engine breather line
installation meets the requirements of §121.243 if the lower breather
lines actually extend to the trailing edge of the oil cooler air exit
duct.
17. Firewalls and firewall construction. Compliance is required
with all of the provisions of §§121.245 and 121.247. The following
requirements must be met in showing compliance with these sections:
(a) Engine compartment. The engine firewalls of the C-46
airplane must --
(1) Conform to type design, and all applicable airworthiness
directives;
(2) Be constructed of stainless steel or approved equivalent; and
(3) Have fireproof shields over the fairleads used for the engine
control cables that pass through each firewall.
(b) Combustion heater compartment. C-46 airplanes must have a
combustion heater fire extinguishing system which complies with AD-49-18-1
or an FAA approved equivalent.
18. Cowling. Standard C-46 engine cowling (cowling of aluminum
construction employing stainless steel exhaust shrouds) which conforms to
the type design and cowling configurations which conform to the C-46
transport category requirements meet the requirements of §121.249.
19. Engine accessory section diaphragm. C-46 engine nacelles
which conform to the C-46 transport category requirements meet the
requirements of §121.251. As provided for in that section, a means of
equivalent protection which does not require provision of a diaphragm to
isolate the engine power section and exhaust system from the engine
accessory compartment is the designation of the entire engine compartment
forward of and including the firewall as a designated fire zone, and the
installation of adequate fire detection and fire extinguishing systems
which meet the requirements of §121.263 and §121.273, respectively, in
such zone.
20. Powerplant fire protection. C-46 engine compartments and
combustion heater compartments are considered as designated fire zones
within the meaning of §121.253.
21. Flammable fluids --
(a) Engine compartment. C-46 engine compartments which conform
to the type design and which comply with all applicable airworthiness
directives meet the requirements of §121.255.
(b) Combustion heater compartment. C-46 combustion heater
compartments which conform to type design and which meet all the
requirements of AD-49-18-1 or an FAA approved equivalent meet the
requirements of §121.255.
22. Shutoff means --
(a) Engine compartment. C-46 engine compartments which comply
with AD-62-10-2 or FAA approved equivalent meet the requirements of
§121.257 applicable to engine compartments, if, in addition, a means
satisfactory to the Administrator is provided to shut off the flow of
hydraulic fluid to the cowl flap cylinder in each engine nacelle. The
shutoff means must be located aft of the engine firewall. The operator's
manual must include, in the emergency portion, adequate instructions for
proper operation of the additional shutoff means to assure correct
sequential positioning of engine cowl flaps under emergency conditions. In
accordance with §121.315, this positioning must also be incorporated in
the emergency section of the pilot's checklist.
(b) Combustion heater compartment. C-46 heater compartments
which comply with paragraph (5) of AD-49-18-1 or FAA approved equivalent
meet the requirements of §121.257 applicable to heater compartments if, in
addition, a shutoff valve located above the main cabin floor level is
installed in the alcohol supply line or lines between the alcohol supply
tank and those alcohol pumps located under the main cabin floor. If all of
the alcohol pumps are located above the main cabin floor, the alcohol
shutoff valve need not be installed. In complying with paragraph (5) of
AD-49-18-1, a fail-safe electric fuel shutoff valve may be used in lieu of
the manually operated valve.
23. Lines and fittings. -- (a) Engine compartment. C-46
engine compartments which comply with all applicable airworthiness
directives, including AD-62-10-2, by using FAA approved fire-resistant
lines, hoses, and end fittings, and engine compartments which meet the
C-46 transport category requirements, meet the requirements of §121.259.
(b) Combustion heater compartments All lines, hoses, and end
fittings, and couplings which carry fuel to the heaters and heater
controls, must be of FAA approved fire-resistant construction.
24. Vent and drain lines. -- (a) Enginecompartment. C-46
engine compartments meet the requirements of §121.261 if --
(1) The compartments conform to type design and comply with all
applicable airworthiness directives or FAA approved equivalent; and
(2) Drain lines from supercharger case, engine-driven fuel pump, and
engine-driven hydraulic pump reach into the scupper drain located in the
lower cowling segment.
(b) Combustion heater compartment. C-46 heater compartments meet
the requirements of §121.261 if they conform to AD-49-18-1 or FAA approved
equivalent.
25. Fire-extinguishing system. (a) To meet the requirements of
§121.263, C-46 airplanes must have installed fire extinguishing systems to
serve all designated fire zones. The fire-extinguishing systems, the
quantity of extinguishing agent, and the rate of discharge shall be such
as to provide a minimum of one adequate discharge for each designated fire
zone. Compliance with this provision requires the installation of a
separate fire extinguisher for each engine compartment. Insofar as the
engine compartment is concerned, the system shall be capable of protecting
the entire compartment against the various types of fires likely to occur
in the compartment.
(b) Fire-extinguishing systems which conform to the C-46 transport
category requirements meet the requirements set forth in paragraph (a).
Furthermore, fire-extinguishing systems for combustion heater compartments
which conform to the requirements of AD-49-18-1 or an FAA approved
equivalent also meet the requirements in paragraph (a).
In addition, a fire-extinguishing system for C-46 airplanes meets the
adequacy requirement of paragraph (a) if it provides the same or
equivalent protection to that demonstrated by the CAA in tests conducted
in 1941 and 1942, using a CW-20 type engine nacelle (without diaphragm).
These tests were conducted at the Bureau of Standards facilities in
Washington, DC, and copies of the test reports are available through the
FAA Regional Engineering Offices. In this connection, the flow rates and
distribution of extinguishing agent substantiated in American Airmotive
Report No. 128-52-d, FAA approved February 9, 1953, provides protection
equivalent to that demonstrated by the CAA in the CW-20 tests. In
evaluating any C-46 fire-extinguishing system with respect to the
aforementioned CW-20 tests, the Administration would require data in a
narrative form, utilizing drawings or photographs to show at least the
following:
Installation of containers; installation and routing of plumbing; type,
number, and location of outlets or nozzles; type, total volume, and
distribution of extinguishing agent; length of time required for
discharging; means for thermal relief, including type and location of
discharge indicators; means of discharging, e.g., mechanical cutterheads,
electric cartridge, or other method; and whether a one- or two-shot system
is used; and if the latter is used, means of cross-feeding or otherwise
selecting distribution of extinguishing agent; and types of materials used
in makeup of plumbing.
High rate discharge (HRD) systems using agents such as
bromotrifluoromethane, dibrodifluoromethane and chlorobromomethane (CB),
may also meet the requirements of paragraph (a).
26. Fire-extinguishing agents, Extinguishing agent container
pressure relief, Extinguishing agent container compartment temperatures,
and Fire-extinguishing system materials. No change from the
requirements of §§121.265 through 121.271.
27. Fire-detector system. Compliance with the requirements of
§121.273 requires that C-46 fire detector systems conform to:
(a) AD-62-10-2 or FAA approved equivalent for engine compartments; and
(b) AD-49-18-1 or FAA approved equivalent for combustion heater
compartments
28. Fire detectors. No change from the requirements of §121.275.
29. Protection of other airplane components against fire. To
meet the requirements of §121.277, C-46 airplanes must --
(a) Conform to the type design and all applicable airworthiness
directives; and
(b) Be modified or have operational procedures established to provide
additional fire protection for the wheel well door aft of each engine
compartment. Modifications may consist of improvements in sealing of the
main landing gear wheel well doors. An operational procedure which is
acceptable to the Agency is one requiring the landing gear control to be
placed in the up position in case of in-flight engine fire. In accordance
with §121.315, such procedure must be set forth in the emergency portion
of the operator's emergency checklist pertaining to in-flight engine fire.
30. Control of engine rotation. C-46 propeller feathering
systems which conform to the type design and all applicable airworthiness
directives meet the requirements of §121.279.
31. Fuel system independence. C-46 fuel systems which conform to
the type design and all applicable airworthiness directives meet the
requirements of §121.281.
32. Induction system ice prevention. The C-46 carburetor
anti-icing system which conforms to the type design and all applicable
airworthiness directives meets the requirements of §121.283.
33. Carriage of cargo in passenger compartments. Section 121.285
is not applicable to nontransport category C-46 cargo airplanes.
34. Carriage of cargo in cargo compartments. A standard cargo
loading and tiedown arrangement set forth in the operator's manual and
found acceptable to the Administrator must be used in complying with
§121.287.
35. Performance data. Performance data on Curtiss model C-46
airplane certificated for maximum weight of 45,000 and 48,000 pounds for
cargo-only operations.
1. The following performance limitation data, applicable to the Curtiss
model C-46 airplane for cargo-only operation, must be used in determining
compliance with §§121.199 through 121.205. These data are presented in the
tables and figures of this appendix.
TABLE 1 -- TAKEOFF LIMITATIONS
(a) Curtiss C-46 certificated for maximum weight of 45,000 pounds.
(1) Effective length of runway required when effective length is
determined in accordance with §121.171 (distance to accelerate to 93 knots
TIAS and stop, with zero wind and zero gradient). (Factor=1.00)
[Distance in feet]
------------------------------------------------------------------------
Airplane weight in pounds
-----------------------------
Standard altitude in feet 45,000
39,000 42,000 \1\
------------------------------------------------------------------------
S.L....................................... 4,110 4,290 4,570
1,000..................................... 4,250 4,440 4,720
2,000..................................... 4,400 4,600 4,880
3,000..................................... 4,650 4,880 5,190
4,000..................................... 4,910 5,170 5,500
5,000..................................... 5,160 5,450 5,810
6,000..................................... 5,420 5,730 6,120
7,000..................................... 5,680 6,000 6,440
8,000..................................... 5,940 6,280 (\1\)
------------------------------------------------------------------------
\1\ Ref. Fig. 1(a)(1) for weight and distance for altitudes above
7,000[foot].
(2) Actual length of runway required when effective length,
considering obstacles, is not determined (distance to accelerate to 93
knots TIAS and stop, divided by the factor 0.85).
[Distance in feet]
------------------------------------------------------------------------
Airplane weight in pounds
-----------------------------
Standard altitude in feet 45,000
39,000 42,000 \1\
------------------------------------------------------------------------
S.L....................................... 4,830 5,050 5,370
1,000..................................... 5,000 5,230 5,550
2,000..................................... 5,170 5,410 5,740
3,000..................................... 5,470 5,740 6,100
4,000..................................... 5,770 6,080 6,470
5,000..................................... 6,070 6,410 6,830
6,000..................................... 6,380 6,740 7,200
7,000..................................... 6,680 7,070 7,570
8,000..................................... 6,990 7,410 (\1\)
------------------------------------------------------------------------
\1\ Ref. Fig. 1(a)(2) for weight and distance for altitudes above
7,000[foot].
(b) Curtiss C-46 certificated for maximum weight 48,000 pounds.
(1) Effective length of runway required when effective length is
determined in accordance with §121.171 (distance to accelerate to 93 knots
TIAS and stop, with zero wind and zero gradient). (Factor=1.00)
[Distance in feet]
------------------------------------------------------------------------
Airplane weight in pounds
---------------------------------------
Standard altitude in feet 48,000
39,000 42,000 45,000 \1\
------------------------------------------------------------------------
S.L............................. 4,110 4,290 4,570 4,950
1,000........................... 4,250 4,440 4,720 5,130
2,000........................... 4,400 4,600 4,880 5,300
3,000........................... 4,650 4,880 5,190 5,670
4,000........................... 4,910 5,170 5,500 6,050
5,000........................... 5,160 5,450 5,810 6,420
6,000........................... 5,420 5,730 6,120 6,800
7,000........................... 5,680 6,000 6,440 (\1\)
8,000........................... 5,940 6,280 6,750 (\1\)
------------------------------------------------------------------------
\1\ Ref. Fig. 1(b)(1) for weight and distance for altitudes above
6,000[foot].
(2) Actual length of runway required when effective length,
considering obstacles, is not determined (distance to accelerate to 93
knots TIAS and stop, divided by the factor 0.85).
[Distance in feet]
------------------------------------------------------------------------
Airplane weight in pounds
---------------------------------------
Standard altitude in feet 48,000
39,000 42,000 45,000 \1\
------------------------------------------------------------------------
S.L............................. 4,830 5,050 5,370 5,830
1,000........................... 5,000 5,230 5,550 6,030
2,000........................... 5,170 5,410 5,740 6,230
3,000........................... 5,470 5,740 6,100 6,670
4,000........................... 5,770 6,080 6,470 7,120
5,000........................... 6,070 6,410 6,830 7,560
6,000........................... 6,380 6,740 7,200 8,010
7,000........................... 6,680 7,070 7,570 (\1\)
8,000........................... 6,990 7,410 7,940 (\1\)
------------------------------------------------------------------------
\1\ Ref. Fig. 1(b)(2) for weight and distance for altitudes above
6,000[foot].
TABLE 2 -- EN ROUTE LIMITATIONS
(a) Curtiss model C-46 certificated for maximum weight of 45,000 pounds
(based on a climb speed of 113 knots (TIAS)).
------------------------------------------------------------------------
Terrain
Weight (pounds) clearance Blower setting
(feet) \1\
------------------------------------------------------------------------
45,000................................ 6,450 Low.
44,000................................ 7,000 Do.
43,000................................ 7,500 Do.
42,200................................ 8,000 High.
41,000................................ 9,600 Do.
40,000................................ 11,000 Do.
39,000................................ 12,300 Do.
------------------------------------------------------------------------
\1\ Highest altitude of terrain over which airplanes may be operated in
compliance with § 121.201.
Ref. Fig. 2(a).
(b) Curtiss model C-46 certificated for maximum weight of 48,000 pounds
or with engine installation approved for 2,550 revolutions per minute
(1,700 brake horsepower). Maximum continuous power in low blower (based on
a climb speed of 113 knots (TIAS)).
------------------------------------------------------------------------
Terrain
Weight (pounds) clearance Blower setting
(feet) \1\
------------------------------------------------------------------------
48,000................................ 5,850 Low.
47,000................................ 6,300 Do.
46,000................................ 6,700 Do.
45,000................................ 7,200 Do.
44,500................................ 7,450 Do.
44,250................................ 8,000 High.
44,000................................ 8,550 Do.
43,000................................ 10,800 Do.
42,000................................ 12,500 Do.
41,000................................ 13,000 Do.
------------------------------------------------------------------------
\1\ Highest altitude of terrain over which airplanes may be operated in
compliance with § 121.201.
Ref. Fig. 2(b).
TABLE 3 -- LANDING LIMITATIONS
(a) Intended Destination.
Effective length of runway required for intended destination
when effective length is determined in accordance with §121.171 with zero
wind and zero gradient.
(1) Curtiss model C-46 certificated for maximum weight of 45,000
pounds. (0.60 factor)
Distance in feet
----------------------------------------------------------------------------------------------------------------
Airplane weight in pounds and approach speeds \1\ in knots
Standard altitude in feet ---------------------------------------------------------------
40,000 V50 42,000 V50 44,000 V50 45,000 V50
----------------------------------------------------------------------------------------------------------------
S.L............................................. 4,320 86 4,500 88 4,700 90 4,800 91
1,000........................................... 4,440 86 4,620 88 4,830 90 4,930 91
2,000........................................... 4,550 86 4,750 88 4,960 90 5,050 91
3,000........................................... 4,670 86 4,880 88 5,090 90 5,190 91
4,000........................................... 4,800 86 5,000 88 5,220 90 5,320 91
5,000........................................... 4,920 86 5,140 88 5,360 90 5,460 91
6,000........................................... 5,040 86 5,270 88 5,550 90 5,600 91
7,000........................................... 5,170 86 5,410 88 5,650 90 5,750 91
8,000........................................... 5,310 86 5,550 88 5,800 90 5,900 91
----------------------------------------------------------------------------------------------------------------
\1\ Steady approach speed through 50-foot height TIAS denoted by symbol V50.
Ref. Fig. 3(a)(1).
(2) Curtiss model C-46 certificated for maximum weight of 48,000
pounds. 1 (0.60 factor.)
Distance in feet
----------------------------------------------------------------------------------------------------------------
Airplane weight in pounds and approach speeds \2\ in knots
Standard altitude in feet ---------------------------------------------------------------
42,000 V50 44,000 V50 46,000 V50 43,000 V50
----------------------------------------------------------------------------------------------------------------
S.L............................................. 3,370 80 3,490 82 3,620 84 3,740 86
1,000........................................... 3,460 80 3,580 82 3,710 84 3,830 86
2,000........................................... 3,540 80 3,670 82 3,800 84 3,920 86
3,000........................................... 3,630 80 3,760 82 3,890 84 4,020 86
4,000........................................... 3,720 80 3,850 82 3,980 84 4,110 86
5,000........................................... 3,800 80 3,940 82 4,080 84 4,220 86
6,000........................................... 3,890 80 4,040 82 4,180 84 4,320 86
7,000........................................... 3,980 80 4,140 82 4,280 84 4,440 86
8,000........................................... 4,080 80 4,240 82 4,390 84 4,550 86
----------------------------------------------------------------------------------------------------------------
\1\ For use with Curtiss model C-46 airplanes when approved for this weight.
\2\ Steady approach speed through 50 height knots TIAS denoted by symbol V503.
Ref. Fig. 3(a)(2).
(b) Alternate Airports.
Effective length of runway required when effective length is
determined in accordance with §121.171 with zero wind and zero gradient.
(1) Curtiss model C-46 certificated for maximum weight of 45,000
pounds. (0.70 factor.)
Distance in feet
----------------------------------------------------------------------------------------------------------------
Airplane weight in pounds and approach speeds \1\ in knots
Standard altitude in feet ---------------------------------------------------------------
40,000 V50 42,000 V50 44,000 V50 45,000 V50
----------------------------------------------------------------------------------------------------------------
S.L............................................. 3,700 86 3,860 88 4,030 90 4,110 91
1,000........................................... 3,800 86 3,960 88 4,140 90 4,220 91
2,000........................................... 3,900 86 4,070 88 4,250 90 4,340 91
3,000........................................... 4,000 86 4,180 88 4,360 90 4,450 91
4,000........................................... 4,110 86 4,290 88 4,470 90 4,560 91
5,000........................................... 4,210 86 4,400 88 4,590 90 4,680 91
6,000........................................... 4,330 86 4,510 88 4,710 90 4,800 91
7,000........................................... 4,430 86 4,630 88 4,840 90 4,930 91
8,000........................................... 4,550 86 4,750 88 4,970 90 5,060 91
----------------------------------------------------------------------------------------------------------------
\1\ Steady approach speed through 50 foot-height-knots TIAS denoted by symbol V50.
Ref. Fig. 3(b)(1).
(2) Curtiss model C-46 certificated for maximum weight of 48,000
pounds. 1 (0.70 factor.)
Distance in feet
----------------------------------------------------------------------------------------------------------------
Airplane weight in pounds and approach speeds \2\ in knots
Standard altitude in feet ---------------------------------------------------------------
42,000 V50 44,000 V50 46,000 V50 48,000 V50
----------------------------------------------------------------------------------------------------------------
S.L............................................. 2,890 80 3,000 82 3,110 84 3,220 86
1,000........................................... 2,960 80 3,070 82 3,180 84 3,280 86
2,000........................................... 3,040 80 3,150 82 3,260 84 3,360 86
3,000........................................... 3,110 80 3,220 82 3,340 84 3,440 86
4,000........................................... 3,180 80 3,300 82 3,410 84 3,520 86
5,000........................................... 3,260 80 3,380 82 3,500 84 3,610 86
6,000........................................... 3,330 80 3,460 82 3,580 84 3,700 86
7,000........................................... 3,420 80 3,540 82 3,670 84 3,800 86
8,000........................................... 3,500 80 3,630 82 3,760 84 3,900 86
----------------------------------------------------------------------------------------------------------------
\1\ For use with Curtiss model C-46 airplanes when approved for this weight.
\2\ Steady approach speed through 50 foot-height-knots TIAS denoted by symbol V50.
Ref. Fig. 3(b)(2).
(c) Actual length of runway required when effective length, considering
obstacles, is not determined in accordance with §121.171.
(1) Curtiss model C-46 certificated for maximum weight of 45,000
pounds. (0.55 factor.)
Distance in feet
----------------------------------------------------------------------------------------------------------------
Airplane weight in pounds and approach speeds \1\ in knots
Standard altitude in feet ---------------------------------------------------------------
40,000 V50 42,000 V50 44,000 V50 45,000 V50
----------------------------------------------------------------------------------------------------------------
S.L............................................. 4,710 86 4,910 88 5,130 90 5,230 91
1,000........................................... 4,840 86 5,050 88 5,270 90 5,370 91
2,000........................................... 4,960 86 5,180 88 5,410 90 5,510 91
3,000........................................... 5,090 86 5,320 88 5,550 90 5,660 91
4,000........................................... 5,230 86 5,460 88 5,700 90 5,810 91
5,000........................................... 5,360 86 5,600 88 5,850 90 5,960 91
6,000........................................... 5,500 86 5,740 88 6,000 90 6,110 91
7,000........................................... 5,640 86 5,900 88 6,170 90 6,280 91
8,000........................................... 5,790 86 6,050 88 6,340 90 6,450 91
----------------------------------------------------------------------------------------------------------------
\1\ Steady approach speed through 50 foot-height-knots TIAS denoted by symbol V50.
Ref. Fig. 3(c)(1).
(2) Curtiss C-46 certificated for maximum weight of 48,000 pounds.
1 (0.55 factor.)
Distance in feet
----------------------------------------------------------------------------------------------------------------
Airplane weight in pounds and approach speeds \2\ in knots
Standard altitude in feet ---------------------------------------------------------------
42,000 V50 44,000 V50 46,000 V50 48,000 V50
----------------------------------------------------------------------------------------------------------------
S.L............................................. 3,680 80 3,820 82 3,960 84 4,090 86
1,000........................................... 3,770 80 3,910 82 4,050 84 4,180 86
2,000........................................... 3,860 80 4,000 82 4,140 84 4,280 86
3,000........................................... 3,960 80 4,090 82 4,240 84 4,380 86
4,000........................................... 4,050 80 4,190 82 4,340 84 4,490 86
5,000........................................... 4,150 80 4,290 82 4,450 84 4,600 86
6,000........................................... 4,240 80 4,400 82 4,560 84 4,710 86
7,000........................................... 4,350 80 4,510 82 4,670 84 4,840 86
8,000........................................... 4,450 80 4,620 82 4,790 84 4,960 86
----------------------------------------------------------------------------------------------------------------
\1\ For use with Curtiss model C-46 airplanes when approved for this weight.
\2\ Steady approach speed through 50 foot-height-knots TIAS denoted by symbol V50.
Ref. Fig. 3(c)(2).
[Doc. No. 4080, 30 FR 258, Jan. 3, 1965; 30 FR 481, Jan. 14,
1965, as amended by Amdt. 121-207, 54 FR 39293, Sept. 25, 1989]
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