# TCDS 4A27: CV Nevada, LLC

- Type: Type certificate data sheet
- Status: Current
- Holder: CV Nevada, LLC
- Revision: 12
- Revised: November 15, 2013
- Product: Aircraft, Large Airplane
- Certification basis: CAR 4b
- Data sheet PDF: https://openairdocs.org/files/sha256/a7/33/a733dbafb10e517b18daef4a91dd13cefafaded47ec2a9d39bc2a54e73dbfec7
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID189566686420261013184349.0001
- Page: https://openairdocs.org/tcds/4A27

## Models (2)

As the data sheet lists them.

- 22 (880)
- 22M (880M)

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
4A27 
Revision 12 
CV Nevada, LLC 
22 
22M 
November 15, 2013 
TY
PE CERTIFICATE DATA SHEET NO. 4A27 
Th
is data sheet which is a part of type certificate No. 4A27 prescribes conditions and limitations under which the product for which 
the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. 
Ty
pe Certificate Holder 
Ty
pe Certificate Holder Record 
CV Nevada, LLC 
5840 West Craig Road, #120-262 
Las Vegas, Nevada 89130 
AeroXin Industries, Inc. 
5840 West Craig Road, #120-262 
Las Vegas, Nevada 89130 
D & R Nev ada, L LC 
5840 West Craig Road, #120-262 
Las Vegas, Nevada 89130 
Lost Bird Aviation Historical Society & Mu seum 
3172 North Rainbow Blvd. 
Las Vegas, Nevada 89108 
Tracor Flight Systems, Inc. 
1326 Fight Line, Hanger 75 
Mojave, California 93501-1665 
G
eneral Dynamics Corporation 
P.O. Box 1950 
San Diego, Ca lifornia  92112 
I - Model 22 (Transport Aircraft), approved May 1, 1960 (See NOTE 4 for explanation of model identification) 
Engines 4 General Electric Turbojet CJ805-3 or CJ805-3A (See NOTE 6 for  explanation of -3A 
installation requirements).  The fuel and  engine limit data are applicable to both the 
-3 and -3A engines  except as noted below.  Intermixing of the -3 and -3A engines on
the same aircraft is not permitted.
Fuel Kerosene, JP-4 and JP-5 type fuels conforming to G.E. Specification  D50TF2-S2.  See 
NOTE 7 regarding use of Phillips anti-icing  additive PFA 55MB. 
Engine limits Static thrust, S.L., standard day: 
Takeoff (5 min.)  11,200 lb. 
Maximum Continuous   9,800 lb. 
Maximum permissible engine rotor operation speed: 
CJ805-3 and -3A   7684 r.p.m. (103%) 
Page No. 1 2 3 4 5 6 7 8 9 
Rev. No. 12 - 8 - 8 - - - -

4A27 2 
Max
imum permissible temperatures 
(1) Turbine exhaust gas temperatures: 
Takeoff (5 min.) 632°C.    1170°F. 
Maximum Continuous 560°C.    1040°F. 
Maximum Transient 
  Takeoff Refer to Section 8, Figure 2, of G.E. 
Operating Instructions GEI 67826 for the 
-3 engine and GEI 67891 for the -3A engine. 
  Starting Refer to Section 8, Figure 1, of G.E. 
Operating Instructions GEI 67826 for the 
-3 engine and GEI 67891 for the -3A engine. 
(2) Oil temperature, scavenge   149°C.     300°F. 
Max
imum permissible compressor air bleed, percentage of total engine airflow: 
Idle to 6340 r.p.m. (85%) 10% 
6714 r.p.m. (90%) to maximum speed   5% 
(Linear variation between 6340 and 6714 r.p.m.) 
Air
speed limits (IAS) Vmo (Maximum Operating) 373K @ S.L. 
        (Mi) 393K @ 23,000 ft. 
Mmo (Maximum Operating above 23,000 ft.)       M = .884 
Vne (Never Exceed) 398K 
Mne (Never Exceed)       M = .884 
Va (Maneuvering) 
(For maneuvering speeds and buffet envelope refer to FAA 
Approved Airplane Flight Manual Certificate Limitation 1-30) 
Vfe (Flaps Down  0 to 20°) 244K M = .60 
(Flaps Down 20 to 30°) 234K M = .56 
(Flaps Down 30 to 40°) 268K M = .70 
(Flaps Down 40 to 50°) 194K M = .400 
Vlo (Landing Gear Operation) 
(Main Landing Gear as a Speedbrake) 373K M = .884 
(Nose Landing Gear Extension) 318K M = .825 
(Landing Gear Retraction Speed) 268K M = .70 
Vle (Landing Gear Extension) 318K M = .825 
V (Landing Gear Door Operation Limitation)  If the landing gear door 
unlocked warning light illuminates during gear retracted flight operations. 
Airspeed must be reduced to: 320K M = .83 
V (Landing Light Extension) 289K 
V (Fuel Jettison Speed) Vmo  Mmo 
V (Inboard Spoilers when used for 
Longitudinal Control) 244K M = .60 
Vmca (minimum Control Speed) (One engine 
in operative), sea level, standard day, 
127,000 lb. gross weight  127K 
Vmca2 (Minimum Control Speed, two engines 
inoperative), standard day, sea level 161K 
V (Maximum Speed for Autopilot Operation) Vmo  Mmo 
C.G
. range Landing Gear Extended or Retracted (3).

4A27 
3 
(1) T
akeoff prohibited within shaded area
(2) The aft C.G. limitations shown in the above chart for the gross weight range
from 80,000 to 130,000 pounds applies to takeoff only.  For airborne or landing
conditions the aft C.G. limitation is 32% MAC FS849.1.
(3) Nose gear retraction moment is -33,122 in.-lb. 
Max
imum weights Ramp weight 185,000 lbs. (1) 
Takeoff weight 184,500 lbs. (1) 
Landing weight 137,000 lbs. (2) 
(Fuel dump valves required for operation 
in excess of maximum landing weight.) 
(See NOTE 1(f)) 
Zero fuel weight 117,000 lbs. 
Three engine ferry 145,000 lbs. 
(1) A
ll weight in excess of 117,000 lbs. must consist of fuel.  All weight in excess of
137,000 lbs. must consist of jettisonable fuel.
(2) Airplanes modified in accordance with General Dynamics Service Bulletin
No. 32-24 and No. 71-1 or 71-5A are approved for 155,000 lbs. maximum
landing weight.  All weight in excess of 155,000 lbs. must consist of jettisonable
fuel.
Max
imum passengers 110 
Fu
el capacity Airplane Serial Nos. 00-1 through 00-20: 
Total 
Refuel (1)    Usable      Arm 
*2 out board main tanks 16695 lb. ea. 16534 lb. ea. FS-924.4 
   (#1 & #4) 
 2 inboard main tanks 20671 lb. ea. 20510 lb. ea. FS-770.5 
   (#1 & #3) 
Ai
rplane Serial Nos. 00-21 and up or airplanes incorporating Convair Service Bulletin 
28-3
A: 
Total 
Refuel (1)    Usable      Arm 
*2 out board main tanks 16695 lb. ea. 16534 lb. ea. FS-924.4 
(#1 & #4)
16 18 20 22 24 26 28 30 32 34 36
8000
9000
10000
11000
12000
13000
14000
15000
16000
17000
18000
19000
LANDIN
G
TAKEOFFINFLIGHT
Maximum takeoff
gross weight
184,500 lbs.
Maximum landing
gross weight
155,000 lbs. After
incorporation of
Service Bulletins
32-24 and 71-1 of 71-5A.
Maximum landing
gross weight
137,000 lbs. prior
to incorporation of
Service Bulletin 32-24,
71-1 or 71-5.
Maximum zero
fuel weight
117,000 lbs.
GROSS
WEIGHT
(POUNDS)
CG - % MAC

4A27 4 
 2 inb oard main tanks 21021 lb. ea. 20860 lb. ea. FS-770.5 
   (#2 & #3) 
(1) "
Total Refuel Capacity" consists of Unusable (drainable and undrainable quantities)
and Usable Fuel.  See NOTE 1 for the disposition of these fuel weights.
* In
cludes replenish tank fuel as each tank system consists of one main and one replenish
tank.
Fue
l weights are based on 7.0 lb. per U.S. Gallon. 
Ma
ximum allowable fuel weight when refueling with high density type fuels is 
75,432 lb.  See NOTE 1(e) for loading limitations. 
Se
rial Nos. eligible (00-) 1 through 15, 17 through 36, 38 through 42, 50, 51, 52, 62  through 65 
II - M
odel 22M (Transport Aircraft), approved July 24, 1961 
Engi
nes 4 General Electric Turbojet CJ805-3B 
Fu
el Kerosene, JP-4 and JP-5 type fuels conforming to G.E. Specification  D50TF2-S2.  See 
NOTE 7 regarding use of Phillips Anti-icing Additive PFA 55MB. 
Eng
ine limits Static thrust, S.L., standard day: 
Takeoff (5 min.)  11,650 lb. 
Maximum Continuous   9,800 lb. 
Max
imum permissible engine rotor operating speeds: 
Normal Operation   7,684 r.p.m. (103%) 
Max
imum permissible temperatures: 
(1) Turbine exhaust gas temperatures:
Takeoff (5 min.) 632°C. 1170°F. 
Maximum Continuous 582°C. 1080°F. 
Maximum Transient 
  Starting Refer to FAA Approved G.E. Operating 
Instructions GEI 67849,Section 8, Figure 1. 
  Takeoff Refer to FAA Approved G.E. Operating 
Instructions GEI 67849, Section 8, Figure 2 
(2) Oil temperature, scavenge 149°C.   300°F. 
Max
imum permissible compressor air bleed, percentage of total engine airflow: 
Idle to 6340 r.p.m. (85%) 10% 
6714 r.p.m. (90%) to maximum speed   5% 
(Linear variation between 6340 and 6714 r.p.m.) 
Air
speed limits (IAS) Vmo (Normal Operating)  374K at S.L. 
        (Mi) 394K at 23,000 ft. 
Mmo (Above 23,000 ft.) M = .884 
Vn
e (Never Exceed) 399K 
Mne (Never Exceed) M = .884 
Va (M
aneuvering) 
(For maneuvering speeds and buffet envelope refer to FAA 
Approved Airplane Flight Manual Certificate Limitation 1-33) 
Vfe (
Flaps extended 22°) 244K M = 0.60 
 (Flaps extended 33°) 234K M = 0.56 
 (Flaps extended 44°) 214K M = 0.48 
 (Flaps extended 55°) 194K M = 0.40 
NOTE: Design speed for 22° deflection is also design speed for

4A27 
5 
lea ding edge slats at all extensions. 
Vlo (
Main L.G. as a Speedbrake) 374K M = 0.884 
(Nose L. G. Extension) 319K M = 0.827 
(L. G. Retraction Speed) 269K M = 0.70 
Vle (
Landing Gear Extension) 319K M = 0.827 
V (
L. G. Door Operation Limitation)  If the L.G. 
door unlocked warning lights illuminate during 
gear retracted flight operations. 
Airspeed must be reduced to: 319K M = 0.827 
V (Landing Light Extension) 289K 
V (Fuel Jettison Speed) Vmo  Mmo 
V (Inboard Spoilers when used for 
Longitudinal Control) 244K M = .60 
Vmca (Minimum Control Speed, one engine 
inoperative, sea level, standard day, 
gross weight 130,000 lb.) 115K 
Vmca2 (Minimum Control Speed, two engines 
inoperative, standard day, sea level 143K 
V (Maximum Speed for Autopilot Operation) Vmo  Mmo 
Sperry AP at max. servo torque 250K 
(low airspeed torque) 
C.G
. range 
(1) T
akeoff prohibited within shaded area
(2) The aft C.G. limitations shown in the above chart for the gross weight range from
80,000 to 130,000 pounds applies to takeoff only.  For airborne or landing
conditions the aft C.G. limitation is 32% MAC.
(3) Retraction of the landing gear moves the C.G. forward approximately 0.08% of the
MAC.
Max
imum weights Ramp weight 193,500 lb. 
Takeoff weight 193,000 lb. 
Landing weight 155,000 lb. 
(Fuel dump valves required for operation 
16 18 20 22 24 26 28 30 32 34 36
80,000
90,000
100,000
110,000
120,000
130,000
140,000
150,000
160,000
170,000
180,000
190,000
TAKEOFFI NFLI G
HT
Maximum takeoff
gross weight
193,000 lbs.
Maximum
gross weight
155,000 pounds
Maximum zero
fuel weight
121,500 lbs.
GROSS
WEIGHT
(POUNDS)
CG - % MAC
14

4A27 6 
in e xcess of maximum landing weight) 
Zero fuel weight   121,500 lb. 
 (All weight in excess of 121,500 lb. must consist of fuel.  All 
 weight in excess of 155,000 lb. must consist of jettisonable fuel.) 
Three engine ferry   155,000 lbs. 
Max
imum passengers 124 
Fu
el capacity Total 
Refuel (1)    Usable      Arm 
*2 out board main tanks 16695 lb. ea. 16534 lb. ea. FS-924.4 
   (#1 & #4) 
2 inboard main tanks 21021 lb. ea. 20860 lb. ea. FS-770.5 
   (#2 & #3) 
Center section tank 13118 lb. 12978 lb. FS-770.5 
NOTE
: The Model 22M aircraft may incorporate either a complete 
 auxiliary fuel system consisting of three inter-connected 
 fuel tight bladder type cells and related plumbing installed 
 in the aircraft wing center section or incorporate provisions 
 only for installing the system. 
(1) "
Total Refuel" capacity consists of Unusable (drainable and
undrainable quantities) and Usable Fuel.  See NOTE 1 for the
disposition of these fuel weights.
*Includes replenish tank fuel as each tank system consists of one
main and one replenish tank.
Fuel weights are based on 7.0 lb. per U.S. gal. 
Str
uctural limits permit use of fuel with densities ranging up to 
7.0 lb./gal.  (See NOTE 1(e) for loading limitations.) 
Se
rial Nos. eligible (00-) 37, 43 through 49, 53 through 61 
Da
ta Pertinent to All Models 
Datum 100  in. fwd. of nose (Nose is Fuselage Station 100) 
MAC 227
.3 in. (L.E. of MAC +776.4 in.) 
Lev
eling means Provisions for lateral and longitudinal leveling are installed in the left main wheel well.  
The lateral leveling lugs are installed on the fwd. bulkhead stiffener along Water Line  
10.0.  The longitudinal leveling lugs are located on the stiffeners of the center line web 
along Water Line 20.0. 
Mi
nimum crew For all flights:  Pilot, Copilot and Flight Engineer.  (See NOTE 3.) 
Max
imum baggage Capacity Maximum Loading (1) C.G. 
Compartment     Station    (lb.)    lb./ft 2  lb. /in. (in.) 
Fw d. belly   375-  603 8960 100 39.3   +489 
Aft. belly 1002-1230 8300 100 39.3 +1111 
(1)
 Rear compartment limited to densities of 20 lb./ft.3 or less.  Higher density items 
must be loaded in compartment where  tie-down rights are provided. 
Oi
l capacity Engine Oil 
Arm 
Inb oard Outboard 
To tal Capacity 42.4 lb. ea. FS678.0 FS864.0 
Usable Oil 23.5 lb. ea. 
Tank System Including 
Unusable Oil   8.9 lb. ea. 
Engine System Oil 10.0 lb. ea.

4A27 
7 
NOTE : The total oil tank capacity is equal to the sum of the "usable" and "tank system 
including unusable oil" (4.20 gal.  at 7.7 lb./gal. each tank). 
Cons
tant Speed Drive and Thrust Reverser (Common Supply) 
Arm 
Inb oard Outboard 
Total Capacity 22.3 lb. ea. 
Usable Oil   8.0 lb. ea. FS667.0 FS853.0 
Reverser Reserve   3.3 lb. ea. 
Tank System Oil   1.9 lb. ea. 
CSD System Oil   4.5 lb. ea. 
Reverser System Oil   4.6 lb. ea. 
NOTE
: The total oil tank capacity is equal to the sum of the usable, and tank 
system and reverser reserve oil (1.72 gal. at 7.7 lb./gal., ea. tank). 
Max
imum operating altitude 41,000 ft. 
Oth
er operating limitations See FAA Approved Airplane Flight Manual. 
Co
ntrol surface movements The airplane must be rigged in accordance with the following FAA Approved Data: 
Dra
wings 22- refer to Model 22, Drawings 30- refer to Model 22M 
(a) C
onvair Dwg. 22-40052 "Operational Data - Rudder," 30-40052 
 "Operational Data - Rudder" 
(b) Convair Dwg. 22-40056 "Operational Data - Rudder Trim," 
 30-40056 "Operational Data - Rudder Trim" 
(c) Convair Dwg. 22-40053, "Operational Data - Elevator" 
(d) Convair Dwg. 22-40066, "Operational Data - Horizontal Stabilizer" 
(e) Convair Dwg. 22-40054, "Operational Data - Aileron and Spoilers" 
(f) Convair Dwg. 22-40067, "Operational Data - Aileron Trim Tab" 
(g) Convair Dwg. 22-40055, "Operational Data - Flaps" 
(h) Convair Dwg. 22-40057, "Operational Data - Power Plant" 
(i) Convair Dwg. 22-40060, "Operational Data - Landing Gear" 
(j) Convair Dwg. 22-40061, "Operational Data - Nose Wheel Steering" 
(k) Convair Dwg. 22-40062, "Operational Data - Brakes" 
(l) Convair Dwg. 22-40063, "Operational Data - Emergency Landing Gear" 
(m) Convair Dwg. 22-40051, "Operational Data - Leading Edge Flaps and Slats" 
Ce
rtification basis CAR 4b dated December 31, 1953; Amendments 4b-1, 4b-2, 4b-3, 4b-4, 4b-5, 4b-6, 
4b-7, 4b-9, 4b-10 thereto, SR-422B and the special condition contained in 
Attachment "A" of FAA letter to Convair dated November 19, 1957. 
Type
 Certificate No. 4A27 issued May 1, 1960. 
Application for Type Certificate dated March 15, 1956 
Co
mpliance with the following optional requirements has been established: 
Di
tching Provisions only 4b.361 
Ice Protection Provisions 4b.640 
Pr
oduction basis Production Certificate No. 605 
Re
quired equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
(see Certification Basis) must be installed in the aircraft for certification.  Convair Report 
ZM-22- 062, "Master Equipment List, Model 22," contains a list of all required 
equipment that must be installed as well as optional equipment installations approved by 
FAA. 
Ser
vice information Convair Report CS-59-022, "Convair 880 Structural Repair Manual" and CS 61-041, 
"Convair Structural Repair Manual for the Model 22M" is FAA Approved.  Service

4A27 8 
Bul letins and other service information, when FAA approved, will carry a statement to 
that effect. 
NOTE
 1. (a) Current weight and balance report, including list of equipment included in certificated empty weight,
and loading instructions must be in each aircraft at the time of original certification and at all times
thereafter except in the case of operators having an approved weight control system.  Convair Report
ZW-22-021- and ZW-22-029-, "Convair Weight and Balance Report," are applicable to Models 22 and
22M, respectively.
(b) Th
e airplane must be loaded so that the C.G. is within the specified limits at all times, with the effects of
fuel use, gear retraction and crew and passenger movement being considered.  See "C.G. Range" for
restrictions on center of gravity limits for takeoff at gross weights below 130,000 lb.
(c) T
he weight of system fuel and oil as defined below and hydraulic fluid, all of which must be included in
the airplane empty weight, is listed in Convair Report ZM-22-062, "Master Equipment List, Model 22. 
Sys
tem Fuel:  The weight of all fuel required to fill all lines and tanks up to the zero fuel point on the  
fuel gages in the most critical flight altitude.  This includes the unusable tank fuel as defined by  
CAR 4b.416. 
Sys
tem Oil Including Usable:  The weight of oil remaining in the engine, constant speed drive, thrust  
reverser, tanks and lines after subtracting the usable and reverser reserve oil from the total capacity.   
These values are noted under "Oil Capacity" and must be added to the empty weight of the airplane. 
(d) T
he "Unusable" fuel is the amount of fuel in the tanks which is unavailable to the engines under critical
flight conditions as defined by CAR 4b.416 and may be obtained by taking the difference between
"total refuel" and "usable" tank capacities shown under "Fuel Capacity."  This "unusable" fuel is
included in System Fuel as indicated in 1(c) above.
(e) F
uel loading and usable procedures are dictated by structural design and to maintain airplane C.G.
within approved limits.  Refer to Convair Report ZW-22-021- or ZW-22- 029-, the specific airplane
weight and balance reports, for loading, takeoff and landing fuel distribution limitations.
(f) Fu
el Jettison:  Fuel jettisoning must be available for operation of the airplane in excess of the maximum
la nding weight.  Refer to FAA Approved Airplane Flight manual for limitations to be observed during
fuel jettison operation.  The unjettisonable fuel must be included in the airplane landing weight, and the
amount of usable fuel remaining in the tanks after complete jettisoning is as follows:
All A
irplanes: 
  Outboard tanks (1 & 4) 3125 lb. ea. 
  Inboard tanks  (2 & 3) 2825 lb. ea. 
We
ights are based on 7.0 lb. per U.S. Gallon. 
NOTE
 2. Reserved. 
NOTE
 3. All replacement seats (crew, passenger and lounge), although they may comply with TSO-C39, must also be 
demonstrated to comply with CAR 4b.358(c).  Other installations, such as berths, buffets, compartments or 
items of mass which could create a hazard to the safety of passengers and crew must also be demonstrated to 
meet the same requirements. 
NOTE
 4. The 22-1 and 22-2 are versions of the basic Model 22, the certification basis for which is Type Certificate 
No. 4A27.  These dash numbers were selected by Convair primarily for contractual and clerical purposes and 
should not be considered to define different models of airplanes.  One version may be converted to another 
by incorporating pertinent required equipment and complete conformity with corresponding approved 
drawings. 
It s
hould be noted that the identification plate in the cockpit identifies the specific airplane version and that 
different Airplane Flight Manuals, primarily the result of different autopilot installations, air conditioning 
system, and electrical system, are applicable.  Accordingly, when converting from one version to another, the 
identification plate must be suitably revised.  The Flight Manual pertinent to the new version must also be 
installed.

4A27 
9 
NOTE
 5. Air Turbine Starter Ground Carts.  Limitations on the use of ground bleed air sources used for starting the 
CJ 805-3 engines have been established and are noted under the recommendation section on Page 13 of 
Convair Report ZK-22004.  "Failure Analysis of the Model 22 Engine Starting System. 
NOTE
 6. (a) The G.E. CJ805-3A engine is a modified -3 engine and is eligible in Model 22-1 and -2 versions when 
Convair Service Bulletin 71-5 dated September 12, 1961, is satisfactorily accomplished.  Supplement C 
to the FAA Approved Airplane Flight Manuals CS 59-019 and CS 59-061 for the Model 22-1 and 22-2 
versions, respectively, is required as part of this installation. 
(b)
 The G.E. CJ805-3A engine may be operated at derated takeoff power in the Model 22 airplane in 
accordance with the Certificate Limitations and Airplane Performance contained in Supplement D to 
General Dynamics/Convair Report CS 59-061 or an FAA approved equivalent. 
NOTE
 7. Phillips anti-icing fuel additive PFA 55MB may be used at a maximum concentration of 0.15% by volume.  
No fuel system anti-icing credit is allowed. 
-------------------E
ND----------------
```

## ADs (23, in force first)

- [AD 75-02-04](https://openairdocs.org/ad/75-02-04): Electrical Appurtenances · D & R Nevada 22, 22M, 30 and 1 more. Effective Jan 24, 1975
- [AD 73-26-10](https://openairdocs.org/ad/73-26-10): Freon Pack Fuses · D & R Nevada 22, 22M and 30A. Effective Feb 1, 1974
- [AD 73-12-08](https://openairdocs.org/ad/73-12-08): Flap Track Support Structure · D & R Nevada 22 and 22M. Effective Jun 12, 1973
- [AD 73-07-03](https://openairdocs.org/ad/73-07-03): Crack in Rudder Boost Actuator · D & R Nevada 22M. Effective Mar 29, 1973
- [AD 72-13-02](https://openairdocs.org/ad/72-13-02): Main Landing Gear Beams · D & R Nevada 22 and 22M. Effective Jun 30, 1972
- [AD 69-19-06](https://openairdocs.org/ad/69-19-06): Landing Gear Axle Beam · D & R Nevada 22 and 22M. Effective Oct 18, 1969
- [AD 65-02-01](https://openairdocs.org/ad/65-02-01): Engine Fuel Supply Tubes · D & R Nevada 22 and 22M. Effective Feb 4, 1965
- [AD 64-12-04](https://openairdocs.org/ad/64-12-04): Engine Start Valve Open Warning System · D & R Nevada 22, 22M, 30 and 1 more. Effective Jul 6, 1964
- [AD 64-05-03](https://openairdocs.org/ad/64-05-03): Aileron Trim Gearbox Assembly · D & R Nevada 22, 22M, 30 and 1 more. Effective Mar 23, 1964
- [AD 63-20-04](https://openairdocs.org/ad/63-20-04): Flap Actuator Screwjacks · D & R Nevada 22 and 22M. Effective Oct 28, 1963
- [AD 63-16-04](https://openairdocs.org/ad/63-16-04): Outboard Foreflaps · D & R Nevada 22 and 22M. Effective Aug 27, 1963
- [AD 62-21-02](https://openairdocs.org/ad/62-21-02): Rudder · D & R Nevada 22 and 22M. Effective Oct 25, 1962
- [AD 62-20-02](https://openairdocs.org/ad/62-20-02): Aileron Override Spring · D & R Nevada 22, 22M, 30 and 1 more. Effective Oct 9, 1962
- [AD 62-18-01](https://openairdocs.org/ad/62-18-01): Rudder Tab Balance Weights · D & R Nevada 22, 22M, 30 and 1 more. Effective Aug 18, 1962
- [AD 62-12-03](https://openairdocs.org/ad/62-12-03): Flap Carriage Support Fittings · D & R Nevada 22 and 22M. Effective May 24, 1962
- [AD 62-07-01](https://openairdocs.org/ad/62-07-01): Balance Board Trunnions · D & R Nevada 22 and 22M. Effective Mar 24, 1962
- [AD 61-25-02](https://openairdocs.org/ad/61-25-02): Engine Starter Warning Indicator · D & R Nevada 22 and 22M. Effective Dec 29, 1961
- [AD 61-22-04](https://openairdocs.org/ad/61-22-04): Cabin Pressurization Static System · D & R Nevada 22 and 22M. Effective Nov 21, 1961
- [AD 61-14-03](https://openairdocs.org/ad/61-14-03): Cartridge Assembly-Rudder Spring · D & R Nevada 22 and 22M. Effective Jul 7, 1961
- [AD 61-14-04](https://openairdocs.org/ad/61-14-04): Forward Rod End · D & R Nevada 22 and 22M. Effective Jul 7, 1961
- [AD 61-13-01](https://openairdocs.org/ad/61-13-01): AC Power Distribution Box · D & R Nevada 22 and 22M. Effective Jun 20, 1961
- [AD 61-10-02](https://openairdocs.org/ad/61-10-02): Engine Mount Support Fitting · D & R Nevada 22 and 22M. Effective May 11, 1961
- [AD 61-07-01](https://openairdocs.org/ad/61-07-01): Foreflaps · D & R Nevada 22 and 22M. Effective Apr 10, 1961

## Registered aircraft by registry model (OpenAirDocs)

- [Convair 22](https://openairdocs.org/model/convair-22): 0 aircraft (registry code 2423302)
- [Convair 22M](https://openairdocs.org/model/convair-22m): 0 aircraft (registry code 2423304)
- [General Dynamics 22M](https://openairdocs.org/model/general-dynamics-22m): 0 aircraft (registry code 3790104)

## STCs approved under this data sheet (48)

- [STC SA2534SW-D](https://openairdocs.org/stc/SA2534SW-D): Replacement of Switch assembly Int'l Inflatables Co. P/N 68748, with DME Corp. P/N L-140 in emergency evacuation slide lighting system.. Astronics Luminescent Systems Inc
- [STC SA2539SW-D](https://openairdocs.org/stc/SA2539SW-D): Replacement of light assembly, International Inflatables Co. P/N68555-1 with DME Corp. EL-104, EL-104A, and EL-104B in emergency slide lighting system.. Astronics Luminescent Systems Inc
- [STC SA863EA](https://openairdocs.org/stc/SA863EA): Incorporation of DME Corporation emergency evacuation slide lighting system. Astronics Luminescent Systems Inc
- [STC SA1093SO](https://openairdocs.org/stc/SA1093SO): Installation of class 'B' or 'E' cargo compartment.. Aeronautical Engineers, Inc
- [STC ST768SO](https://openairdocs.org/stc/ST768SO): Installation of cargo loading door(forward L.H. side of fuselage).. Aeronautical Engineers, Inc
- [STC ST988SO](https://openairdocs.org/stc/ST988SO): Fabrication and installation of a cargo rack/net assembly.. Page AvJet Corp
- [STC SA1146EA](https://openairdocs.org/stc/SA1146EA): Installation of two Solar APU's Model T-62T-40C.  Limited to installation on Convair 22M, serial number 61.. PATS Aircraft LLC
- [STC SA1072NW](https://openairdocs.org/stc/SA1072NW): Increase of zero fuel weight to131,000 pounds for aircraft complying complying with GD Convair strength and operating restrictions report ZS-22-300, Rev 3.  This STC is limited to aircraft modified per STC Number SA1071NW.. Lost Birds Aviation Historical Society & Museum
- [STC SA1282WE](https://openairdocs.org/stc/SA1282WE): Dual Collins AL101 radio altimeter system, dual Collins No. 51RV-1 navigation receivers and all weather landing system wiring and installation provisions.. Lost Birds Aviation Historical Society & Museum
- [STC SA1-562](https://openairdocs.org/stc/SA1-562): CJ805-3B modified as an alternate to CJ805-3 engine.. Northeast Airlines Inc
- [STC SA2728WE](https://openairdocs.org/stc/SA2728WE): Incorporation of Holcombe Industries HI-LITE SYSTEM P/N 50-1001 for emergency evacuation slide lighting. (707 AIRPLANES EQUIPPED WITH BOEING P/N 65-11685 AND 65-68862 FORWARD THRUST REVERSER DOORS). Maravia Corp of Idaho
- [STC ST944SO](https://openairdocs.org/stc/ST944SO): Installation of (1) Class 'B' cargo compartment, (2) cargo restraining bulkhead, and (3) smoke detector system. STC ST906SO is a required part of this STC. (22M 880). Aeronautical Engineers, Inc
- [STC SA2462SW](https://openairdocs.org/stc/SA2462SW): Installation of interior.. Foster-Edwards Aircraft Co Inc
- [STC SA152GL](https://openairdocs.org/stc/SA152GL): Installation of X band weather radome only on models with Convair22-71001-1 support assembly(bulk-head assembly).. Norton Company, Performance Plactics
- [STC SA36NW](https://openairdocs.org/stc/SA36NW): Installation of Sundstrand Ground Proximity Warning System. Sundstrand Data Control Inc
- [STC SA2549WE](https://openairdocs.org/stc/SA2549WE): The installation of automatically deployable and automatically inflatable emergency exit slides. (22 CV-880). Intl Inflatables Co
- [STC SA830CE](https://openairdocs.org/stc/SA830CE): Install Butler National Corporation flight recorder/ communications interface unit.. Trans World Airlines Inc
- [STC SA772CE](https://openairdocs.org/stc/SA772CE): Installation of Bendix P/N1978128-1 indicator and P/N1964771-3 inverter.. Trans World Airlines Inc
- [STC SA2341WE](https://openairdocs.org/stc/SA2341WE): Installation of battery-powered emergency exit lighting on forward and aft entry and service doors.. Intl Inflatables Co
- [STC SA593CE](https://openairdocs.org/stc/SA593CE): Modification of interior emergency lighting and installation of exterior emergency lighting system. (22 -1 (880)). Trans World Airlines Inc
- [STC SA594CE](https://openairdocs.org/stc/SA594CE): Installation of dual low range radio altimeter system single equipment driving dual indicators.. Trans World Airlines Inc
- [STC SA279CE](https://openairdocs.org/stc/SA279CE): Fairchild cockpit voice recorder system.. Trans World Airlines Inc
- [STC SA1365WE](https://openairdocs.org/stc/SA1365WE): Modification of wiring and equipment installation.. Lear Siegler Inc
- [STC SA214CE](https://openairdocs.org/stc/SA214CE): Autothrust system.. Trans World Airlines Inc
- [STC SA215CE](https://openairdocs.org/stc/SA215CE): Single SCAT system.. Trans World Airlines Inc
- [STC SA216CE](https://openairdocs.org/stc/SA216CE): Autopilot variable angle intercept.. Trans World Airlines Inc
- [STC SA217CE](https://openairdocs.org/stc/SA217CE): Second flight director system.. Trans World Airlines Inc
- [STC SA223CE](https://openairdocs.org/stc/SA223CE): Dual low range radio altimeter system.. Trans World Airlines Inc
- [STC SA241EA](https://openairdocs.org/stc/SA241EA): Nose cap weather radome shell.. McMillan Radiation Labs Inc
- [STC SA280CE](https://openairdocs.org/stc/SA280CE): Autothrust system equipment.. Trans World Airlines Inc
- [STC SA281CE](https://openairdocs.org/stc/SA281CE): Single SCAT system provisions.. Trans World Airlines Inc
- [STC SA281WE](https://openairdocs.org/stc/SA281WE): Engine-mounted fire detector system.. Trans World Airlines Inc
- [STC SA308WE](https://openairdocs.org/stc/SA308WE): Voice interruption priority system.. Northrop Corporation
- [STC SA336SO](https://openairdocs.org/stc/SA336SO): Cockpit voice recorder.. Delta Airlines Inc
- [STC SA376SO](https://openairdocs.org/stc/SA376SO): Relocation of LAS 109C flight recorder and installation of a remote accelerometer.. Delta Airlines Inc
- [STC SA389CE](https://openairdocs.org/stc/SA389CE): Eclipse-Pioneer 15470, 15492 and18729 autopilot amplifier.. Trans World Airlines Inc
- [STC SA390CE](https://openairdocs.org/stc/SA390CE): Eclipse-Pioneer 18729 autopilot amplifier.. Trans World Airlines Inc
- [STC SA484CE](https://openairdocs.org/stc/SA484CE): Relocation of Lockheed Aircraft Service Model 109CR flight recorder.. Trans World Airlines Inc
- [STC SA563CE](https://openairdocs.org/stc/SA563CE): Installation of static port heater system.. Trans World Airlines Inc
- [STC SA579EA](https://openairdocs.org/stc/SA579EA): Replace Bendix type 15866, 15897 and 19903 vertical gyros with Bendix type 19911 or 19912 ertical gyros. (22 -1 (880)). Trans World Airlines Inc
- [STC SA671CE](https://openairdocs.org/stc/SA671CE): Install logo lights in upper leading edges of horizontal stabilizer.. Trans World Airlines Inc
- [STC SA687SW](https://openairdocs.org/stc/SA687SW): Nose cap weather radome shell.. McMillan Radiation Labs Inc
- [STC SA727CE](https://openairdocs.org/stc/SA727CE): Installation of Kollsman altitude alerting system.. Trans World Airlines Inc
- [STC SA896WE](https://openairdocs.org/stc/SA896WE): Rain repellent system.. Jay- Dee Aircraft Supply Co
- [STC SA91SO](https://openairdocs.org/stc/SA91SO): Modification of rotating field element G.E. 291C777G1 of G.E. 400 cycle alternator 2CM211A1.. Peninsular Armature Works Inc.
- [STC ST402SO](https://openairdocs.org/stc/ST402SO): Modification of interior emergency lighting.. Delta Airlines Inc
- [STC ST403SO](https://openairdocs.org/stc/ST403SO): Installation of exterior emergency lighting system.. Delta Airlines Inc
- [STC ST422SO](https://openairdocs.org/stc/ST422SO): Installation of single radar altimeter system. (22M 880). Delta Airlines Inc

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