# TCDS A-762: The Boeing Company

- Type: Type certificate data sheet
- Status: Current
- Holder: The Boeing Company
- Revision: 21
- Revised: September 27, 2010
- Product: Aircraft, Large Airplane
- Registered aircraft: 4, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/e0/01/e0013ebbb96c17b963c1e5d5e714c1a9c12e918e093cc9be885c15361642ce3f
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/CF1BA95763DE5F24862577DD0069B5F7.0001
- Page: https://openairdocs.org/tcds/A-762

## Models (7)

As the data sheet lists them.

- C54E-DC
- C54G-DC
- C54B-DC
- DC-4
- C54A-DC
- C54D-DC
- C54-DC

## What the data sheet says

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

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 
Rev. No. 21 - - - - - - - - - - - - - - - - - - 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A-762 
Revision 21 
 
BOEING 
 C54-DC (Army C-54, Navy R5D) 
 C54A-DC (Army C-54A, Navy R5D-1) 
 C54B-DC (Army C-54B, Navy R5D-2) 
 C54D-DC (Army C-54D, Navy R5D-3) 
 C54E-DC (Army C-54E, Navy R5D-4) 
 C54G-DC (Army C-54G, Navy R5D-5) 
 DC-4 
 
September 27, 2010 
 
AIRCRAFT SPECIFICATION NO. A-762 
 
Type Certificate Holder The Boeing Company 
 4000 Lakewood Boulevard 
 Long Beach, California 90808 
 
Type Certificate Holder Record McDonnell Douglas Cor poration, Long Beach, California merged with The Boeing 
Company in 1997.  Transferred Type Certificate to The Boeing Company on 
September 27, 2010. 
 
Douglas Aircraft Company, Inc., Santa Monica, California merged with McDonnell 
Aircraft Corporation August 25, 1967 
 
I.  Model C54-DC, Approved June 6,  1946.    See NOTE 4 regarding modifications required for conversion of military 
models, and NOTE 10 regarding additional speed and load factor limits. 
 
Engines See Item 100. 
 
Fuel See Item 100. 
  
Engine Limits See Item 100. 
 
Airspeed Limits See Table “B”, NOTE 9. 
 
C.G. Range 16% MAC (381.4) to 32% MAC (407.6) .  Range based on “landing gear extended” and 
 applies for take-off, flight and landing.   
 See NOTE 8 regarding extension of  rear limit for enroute operation. 
 
Maximum Weights See Table “A”, NOTE 9.  For 3-engine ferrying, see NOTE 13. 
 
Minimum Crew 2 - Pilot and co-pilot at +108.0 
 
Passengers Variable, see approved loading sche dule.  See NOTE 6 regarding emergency exit  
 requirements. 
 
Maximum Baggage Cu. Ft . Weight  Arm  
Forward Belly 130 2100 lbs. (+228.2) 
Aft Belly 151 2520 lbs. (+590.5) 
Crew Room  1500 lbs. (+228.2) 
Coat Closet 106   500 lbs. (+746.5)

Fuel Capacity (without 2 inboard inner wi ng tanks 497 gal. ea. 2982 lbs. ea. (+400.9) 
  Stoner-Mudge Sealing) 2 outboard inner wi ng tanks 425 gal. ea. 2550 lbs. ea. (+404.1) 
  2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+228.2) 
   (when installed, see NOTE 9) 
  Fuselage Fuel Tanks 464 ga l. ea. 2784 lbs. ea. (+301.0) 
                    and (+381.0) 
 
  When Stoner-Mudge Sealing is incorporat ed, see pertinent report referred to in 
  NOTE 4. 
 
Oil Capacity 20 gals. in each inboard nacelle  150 lbs. ea.  (+327.0) 
  20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 
  50 gals. in fuselage tank  375 lbs. (+223.3) 
   See NOTE 7 regarding fuel load when fuselage oil tank is removed. 
 
Serial Nos. Eligible 3050 to 3053 including, 3060 to 3063 including, 3075 and 3111 to 3125 inclusive. 
 
Required Equipment 1(a), 100(a), 102(d) , 200, 201, 202, 203, 204, 205, 400, 401. 
 
Optional Equipment 1(b), 100(b), (c), (d), (e), (f),  or (g), 101, 102(b), (c), (f), or (h), 402, 500. 
 
 
II.  Model C-54A-DC, Approved June 6,  1946.  See NOTE 4 regarding modifications required for conversion of military 
models and NOTE 10 regarding additional speed and load factor limits. 
(Same as C54-DC except for large fuselage door, heavier fuselage plating and stringers, heavier cargo floors and floor beams,  
increased strength of center wing and cargo and troop carrying provision.) 
 
Engine See Item 100. 
 
Fuel See Item 100. 
 
Engine Limits See Item 100. 
 
Airspeed Limits See Table “B”, NOTE 9. 
 
C.G. Range 16% MAC (381.4) to 32% MAC (407.6) .  Range based on “landing gear extended” and 
  applies for take-off, flight and landing. 
  See NOTE 8 regarding extension of  rear limit for enroute operation. 
 
Maximum Weights See Table “A”, NOTE 9.  For 3-engine ferrying, see NOTE 13. 
 
Minimum Crew 2 - Pilot and co-pilot at +108.0 
 
Passengers Variable, see approved loading sche dule.  See NOTE 6 regarding emergency exit 
  requirements. 
 
Maximum Baggage  Cu. Ft. Weight   Arm  
Forward Belly 130 2100 lbs. (+228.2) 
Aft Belly 151 2520 lbs. (+590.5) 
Crew Room  1500 lbs. (+228.2) 
   Cabin Floor Loadings (Do not exceed either value shown) 
   
   Sta. 129-260 1/2     100#/ft 2 or 50#/in. lengthwise of cabin. 
   Sta. 260 1/2-680     200#/ft 2 or 80#/in. lengthwise of cabin. 
   Sta. 680-858           100#/ft 2 or 30#/in. lengthwise of cabin. 
 
Fuel Capacity (without Storner- 2 inboard inne r wing tanks 508 gal. ea. 3048 lbs. ea.  (+400.9) 
 Mudle Sealing) 2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea. (+404.1) 
  2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+228.2) 
  Fuselage Fuel Tanks 464 ga l. ea. 2784 lbs. ea. (+301.0) 
                    and (+381.0)

A-762 3
  (When Stoner-Mudge Sealing is incorporat ed, see pertinent report referred to in 
  NOTE 4.) 
 
Oil Capacity 20 gals. in each inboard nacelle  150 lbs. ea.  (+327.0) 
  20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 
  50 gals. in fuselage tank  375 lbs. (+223.3) 
  See NOTE 7 regarding fuel load wh en fuselage oil tank is removed. 
 
Serial Nos. Eligible 3054 to 3059 inclusive, 3064 to  3074 inclusive, 3076 to 3110 inclusive, 7445 to 7469  
  inclusive, 7471 to 7489 inclusive, 10270 to 10424 inclusive. 
 
Required Equipment 1(a), 100(a), 102(e) , 200, 201, 202, 203, 204, 205, 400,401. 
 
Optional Equipment 1(b), 100(b), (c), (d), (e), (f), or (g), 101, 102(b), (c), (d), (f) or (h), 402, 500. 
 
 
III.  Model C54B-DC, Approved June 6,  1946.  See NOTE 4 regarding modifications required for conversion of military 
models, and NOTE 10 regarding additional speed and load factor limits. 
(Same as the Model C54A-DC, except that outer wing panels incorporate integral fuel tanks and only two fuselage fuel tanks 
were originally installed.) 
 
Engines See Item 100 
 
Fuel See Item 100 
 
Engine Limits See Item 100 
 
Airspeed Limits See Table “B”, NOTE 9 
 
C.G. Range 16% MAC (381.4) to 32% MAC (407.6) .  Range based on “landing gear extended” and 
  applies for take-off, flight and landing. 
  See NOTE 8 regarding extension of  rear limit for enroute operation. 
 
Maximum Weights See Table “A”, NOTE 9.  For 3-engine ferrying, see NOTE 13. 
 
Minimum Crew 2 - Pilot and co-pilot at +108.0 
 
Passengers Variable, see a pproved loading schedule. 
  
Maximum Baggage  Cu . ft. Weight Arm  
Forward Belly 130 2100 lbs. (+228.2) 
Aft Belly 151 2520 lbs. (+590.5) 
Crew Room  1500 lbs. (+228.2) 
   Cabin Floor loadings (Do not exceed either value shown). 
 
   Sta. 129-260 1/2      100#/ft 2 or 50#/in. lengthwise of cabin. 
   Sta. 260 1/2-680      200#/ft 2 or 80#/in. lengthwise of cabin. 
   Sta. 680-858            100#/ft 2 or 30#/in. lengthwise of cabin. 
 
Fuel Capacity (Without Stoner- 2 inboard inner wing tanks 508 gal. ea.  3048 lbs. ea.  (+400.9) 
 Mudge Sealing) 2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea. (+404.1) 
  2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+404.5) 
  Fuselage Fuel Tanks 464 ga l. ea. 2784 lbs. ea. (+301.0) 
                   and (+381.0) 
  (When Stoner-Mudge Sealing is in corporated, see pertinent report 
   referred to in NOTE 4.) 
 
Oil Capacity 20 gals. in each inboard nacelle  150 lbs. ea. (+327.0) 
  20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 
  50 gals. in fuselage tank  375 lbs. (+223.3) 
  See NOTE 7 regarding fuel load wh en fuselage oil tank is removed.

Serial Nos. Eligible 18324 to 18398inclusive , 27227 to 27251 inclusive, 10425 to 10544 inclusive 
 
Required Equipment 1(a), 100(a), 102(c) , 200, 201, 202, 203, 204, 205, 400, 401. 
Optional Equipment 1(b), 100(b), (c), (d), (e ), (f), or (g), 101, 102(b), or (h), 402, 500 
 
IV.  Model C54D-DC, Approved June 6,  1946.  See NOTE 4 regarding modifications required for conversion of 
military models and NOTE 10 regarding additional speed and load factor limits. 
(Essentially same as C54B-DC except R-2000-7 and R-2000-11 engines installed in C54D-DC while R-2000-7 engines 
originally installed in C54B-DC.) 
 
Engines See Item 100 
 
Fuel See Item 100 
 
Engine Limits See Item 100 
 
Airspeed Limits See Table “B”, NOTE 9 
 
C.G. Range 16% MAC (381.4) to 32% MAC (407.6) .  Range based on “landing gear extended” and 
  applies for take-off, flight and landing.   
  See NOTE 8 regarding extension of  rear limit for enroute operation. 
 
Maximum Weights See Table “A”, NOTE 9.  For 3-engine ferrying, see NOTE 13.  
 
Minimum Crew 2 - Pilot and co-pilot at +108.0 
 
Passengers Variable, see a pproved loading schedule. 
 
Maximum Baggage  Cu . Ft. Weight  Arm  
Forward Belly 130 2100 lbs. (+228.2) 
Aft Belly 151 2520 lbs. (+590.5) 
Crew Room  1500 lbs. (+228.2) 
   Cabin Floor loadings (Do not exceed either value shown.) 
 
   Sta. 129-260 1/2     100#/ft 2 or 50#/in. lengthwise of cabin 
   Sta. 260 1/2-680     200#/ft 2 or 80#/in. lengthwise of cabin 
   Sta. 680-858           100#/ft 2 or 30#/in. lengthwise of cabin 
 
Fuel Capacity (Without Stoner- 2 inboard inne r wing tanks 508 gal. ea. 3048 lbs. ea. (+400.9) 
 Mudge Sealing) 2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea. (+404.1) 
  2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+404.5) 
  Fuselage Fuel Tanks 464 ga l. ea. 2784 lbs. ea. (+301.0) 
  (When Stoner-Mudge Sealing is incorporat ed, see pertinent report referred to in  
  NOTE 4.) 
 
Oil Capacity 20 gals. in each inboard nacelle  150 lbs. ea.  (+327.0) 
  20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 
  50 gals. in fuselage tank  375 lbs.  (+223.3) 
  See NOTE 7 regarding fuel load wh en fuselage oil tank is removed. 
 
Serial Nos. Eligible 10545 to 10869 inclusive, 22149 to 22203 inclusive 
 
Required Equipment 1(a), 100(c), 102(c) , 200, 201, 202, 203, 204, 205, 400, 401. 
 
Optional Equipment 1(b), 100(a), (b), (d), (e ), (f), or (g), 101, 102(b), or (h), 402, 500

A-762 5
V.  Model C54E-DC, Approved June 6,  1946.  See NOTE 4 regarding modifications required for conversion of military 
models and NOTE 10 regarding additional speed and load factor limits. 
(Same as C54B-DC except for engine installation, omission of remaining fuselage tanks, fuel cells installed in center wing 
between inboard nacelle and side of fuselage, installation of soundproofing, cabin upholstering, buffet, lounge in rear of cabin 
and removable passenger seats.) 
 
Engines See Item 100. 
 
Fuel See Item 100. 
 
Engine Limits See Item 100. 
 
Airspeed Limits See Table “B”, NOTE 9. 
 
C.G. Range 16% MAC (381.4) to 32% MAC (407.6) .  Range based on “landing gear extended” and 
  applies for take-off, flight and landing. 
  See NOTE 8 regarding extension of  rear limit for enroute operation. 
 
Maximum Weights See Table “A”, NOTE 9.  For 3-engine ferrying, see NOTE 13. 
 
Minimum Crew 2 - Pilot and co-pilot at +108.0 
 
Passengers Variable, see approved loading schedule 
 
Maximum Baggage  Cu . ft. Weight Arm  
Forward Belly 130 2100 lbs. (+228.2) 
Aft Belly 151 2520 lbs. (+590.5) 
Crew Room  1500 lbs. (+228.2) 
Rear Cabin    500 lbs. (+711.2) 
Coat Closet    200 lbs. (+795.0) 
   Cabin Floor loadings (Do not exceed either value shown) 
 
   Sta. 129-260 1/2      100#/ft 2 or 50#/in. lengthwise of cabin. 
   Sta. 260 1/2-680      200#/ft 2 or 80#/in. lengthwise of cabin. 
   Sta. 680-858            100#/ft 2 or 30#/in. lengthwise of cabin. 
 
Fuel Capacity (Without Stoner- 
 Mudge Sealing) 2 inboard inner wing tanks 508 gal. ea. 3048 lbs. ea. (+400.9) 
  2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea. (+404.1) 
  2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+404.5) 
  2 inner wing fuel cells 362 gal. ea. 2172 lbs. ea. (+397.5) 
  (When Stoner-Mudge Sealing is in corporated, see pertinent report  
   referred to in NOTE 4. 
 
Oil Capacity 20 gals. in each inboard nacelle  150 lbs. ea. (+327.0) 
  20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 
  50 gals. in fuselage tank  375 lbs. (+223.3) 
  See NOTE 7 regarding fuel load wh en fuselage oil tank is removed. 
 
Serial Nos. Eligible 27242 to 27376 inclusive 
 
Required Equipment 1(a), 100(b), 102(a) , 200, 201, 202, 203, 204, 205, 400, 401 
 
Optional Equipment 1(b), 100(a), (c), (d), (e),  (f), or (g), 101, 102(g) or (h), 402, 500.

VI.  Model C54G-DC, Approved June 6,  1946.  See NOTE 4 Regarding modifications required for conversion of military 
models, and NOTE 10 regarding additional speed and load factor limits. 
(Same as C54E-DC, except troop carrying provisions installed instead of passenger interior.) 
 
Engines See Item 100. 
 
Fuel See Item 100. 
 
Engine Limits See Item 100. 
 
Airspeed Limits See Table “B”, NOTE 9. 
 
C.G. Range 16% MAC (381.4) to 32% MAC (407.6).  Range based on “landing gear extended” and  
  applies for take-off, flight and landing. 
  See NOTE 8 regarding extension of  rear limit for enroute operation. 
 
Maximum Weights See Table “A”, NOTE 9.  For 3-engine ferrying, see NOTE 13. 
 
Minimum Crew 2 - Pilot and co-pilot at +108.0 
 
Passengers Variable, see a pproved loading schedule. 
 
Maximum Baggage  Cu . Ft. Weight Arm  
Forward Belly 130 2100 lbs. (+228.2) 
Aft Belly 151 2520 lbs. (+590.5) 
Crew Room  1500 lbs. (+228.2) 
    Cabin Floor Loadings (Do not exceed either value shown). 
 
    Sta. 129-260 1/2      100#/ft 2 or 50#/in. lengthwise of cabin. 
    Sta. 260 1/2-680      200#/ft 2 or 80#/in. lengthwise of cabin. 
    Sta. 680-858            100#/ft 2 or 30#/in. lengthwise of cabin. 
 
Fuel Capacity (Without Stoner- 
 Mudge Sealing) 2 inboard inner wing tanks 508 gal. ea. 3048 lbs. ea. (+400.9) 
  2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea. (+404.1) 
  2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+404.5) 
  2 inner fuel cells 362 gal. ea. 2172 lbs. ea. (+397.5) 
  (When Stoner-Mudge Sealing is in corporated, see pertinent report 
   referred to in NOTE 4. 
 
Oil Capacity 20 gals. in each inboard nacelle  150 lbs. ea.  (+327.0) 
  20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 
  50 gals. in fuselage tank  375 lbs.  (+223.3) 
  See NOTE 7 regarding fuel load wh en fuselage oil tank is removed. 
 
Serial Nos. Eligible 35929 to 36090 
 
Required Equipment 1(a), 100(b), 102(a) , 200, 201, 202, 203, 204, 205, 400, 401 
 
Optional Equipment 1(b), 100(a), (c), (d), (e ), (f) or (g), 101, 102(g) or (h), 402, 500

A-762 7
VII.  Model DC-4, Approved June 6,  1946.  See NOTE 10 regarding additional speed and load factor limits. 
 
Engine See Item 100 
 
Fuel See Item 100 
Engine Limits See Item 100 
 
Airspeed Limits See Table “B”, NOTE 9 
 
C.G. Range 16% MAC (381.4) to 32% MAC (407.6).  Range based on “landing gear extended” and  
  applies to take-off, flight and landing. 
  See NOTE 8 regarding extension of  rear limit for enroute operation. 
 
Maximum Weights See Table “A”, NOTE 9.  For 3-engine ferrying, see NOTE 13. 
 
Minimum Crew 2 - Pilot and Co-pilot at +108.0 
 
Passengers Variable, see a pproved loading schedule. 
 
Maximum Baggage 
 Cu. Ft. Weight  Arm 
Forward Belly 130 2100 lbs. (+228.2) 
Aft Belly 151 2520 lbs. (+590.5) 
Left Hand Forward    
    (Sta. 171-260) Dwg. 5326973 2210 lbs. (+212.5) or 
    (Sta. 164.5-620) Dwg. 5326376,   
    5326376-500, 5326791 and 5326646 2320 (+212.5) or 
    (Sta. 218.5-260) Dwg. 5326646 1110 lbs. (+239.3) or 
    (Sta. 193.5-260) Dwg. 5327107 1760 lbs. (+227.3) or 
    (Sta. 129.0-214.5) Dwg. 5326809 1700 lbs. (+171.5) 
Right Hand Forward   
    (Sta. 184.0-260) Dwg. 5326791,   
     5327107, 5326810, 5326811,   
     5338233, 5338179 (Oil Tank   
     Installed) 1300 lbs. (+222.0) or 
    (Sta. 171.5-260) Dwg. 5326646   
    (Oil Tank Installed) 1470 lbs. (+219.2) or 
    (Sta. 171.0-260) Dwg. 5326376,   
    5326809 (Oil Tank Installed) 1610 lbs. (+215.5) 
    With Oil Tank Removed, Dwg.   
    5326376-500, 5326973 2270 lbs. (+215.5) 
Aft Center Closet    
    (Sta. 828.0-858.0) Dwg. 5326750   200 lbs. (+843.0) 
Aft Left Closet    
   (Sta. 732.0-806.0) Dwg. 5326171   200 lbs. (+763.0) or 
   (With tiedowns, capacity may be increased to 600 lbs.)  
   (Sta. 742.5-806.5) Dwg. 5326965   200 lbs. (+774.5) or 
   (Sta. 768.5)  Dwg. 5326538   200 lbs. (+787.5) or 
   (Sta. 781.5-809.5) Dwg. 5327444   200 lbs. (+770.5) or 
   (Sta. 788.0-812.0) Dwg. 533681,   
     5240767   200 lbs. (+800.0) 
Aft Right Closet    
   (Sta. 750.0-806.0) Dwg. 5327319   200 lbs. (+778.0) 
    Cabin Floor Loadings (Do not exceed either value shown) 
 
    Sta. 129-260 1/2      100#/ft 2 or 50#/in. lengthwise of cabin. 
    Sta. 260 1/2-680      200#/ft 2 or 80#/in. lengthwise of cabin. 
    Sta. 680-858            100#/ft 2 or 30#/in. lengthwise of cabin.

Fuel Capacity (Without Stoner- 
 Mudge Sealing) 2 inboard inner wing ta nks 508  gal. ea. 3048 lbs. ea. (+400.9) 
  2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea.  (+404.1) 
    2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+404.5) 
  2 inner wing fuel cells 362 gal. ea.  2172 lbs. ea. (+397.5) 
  (When Stoner-Mudge Sealing is inco rporated, the actual capacity of each 
  tank must be determined, and airplane placarded accordingly.) 
 
Oil Capacity 20 gals. in each inboard nacelle  150 lbs. ea.  (+327.0) 
  20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 
  50 gals.  in fuselage area  375 lbs. (+223.3) 
  See NOTE 7 regarding fuel load wh en fuselage oil tank is removed. 
 
Serial Nos. Eligible 42904 and up 
 
Required Equipment 1(a), 100(d), 102(a) , 200, 201, 202, 203, 204, 205, 400, 401. 
 
Optional Equipment 1(b), 100(a), (b), (c), (e ), (f), or (g), 101, 102(g), or (h), 402, 500 
 
Specifications Pertinent to All Models 
 
Datum 3 inches aft of nose 
 
MAC 163.6 in. L.E. of MAC is (+355.2) 
 
Leveling Means Leveling brackets are located in th e nose wheel well and aft of the aft belly cargo 
  compartment.  The rear leveling br acket may be reached through the access door 
  in the aft bulkhead cargo compartment. 
 
Control Surface Rudder  20 
  Elevators 25  up, 15 down 
  Ailerons 15  up, 11 1/2 down 
  Flaps 45  down 
  All trim tabs   15 
 
Certification Basis Type Certificate No. 762 (Com bination CAR 4a dated November 1,  1943, and  
  4b dated November 9,  1945) 
  Compliance with the ditching provisions of 4b.292 (4b.261) has been demonstrated. 
 
Production Basis Production Certificate No. 27 
 
Export Eligibility Eligible for export to all countries  subject to the provisions of MOP 2-4, except as 
  follows: 
   Canada - landplane only eligible 
 
Equipment 
 
Propellers and Propeller Accessories (Except Deicing Equipment) 
 1. 4 propellers 
  (a) Ham. Std., hubs 23E50, blades 6507-0   1852 lb. (+262.2) 
   (To be used on P & W engines only) 
   For interchangeable blade models , see Propeller Spec. No. 603 (NOTE 6) 
   Diameter Max 13’3/8”, min.  allowable for repairs 12’9” 
     No further reduction permitted 
   Min. low pitch setting at 42 in. sta.  21  
   Placard required for all P & WA Twin Wasp and R-2000 series engines  (See NOTE 2b)

A-762 9
Propellers and Propeller Accessories (Except Deicing Equipment)  (cont’d) 
 1. (b) Ham. Std., hubs 23E50, blades 6519-12   1792 lb. (+262.7) 
   (To be used on Wright 736C9HD1 engines only) (See NOTE 2e) 
   For interchangeable blade models , see Propeller Spec. No. 603 (NOTE 6) 
   Diameter Max. 12’1/4”, min.  allowable for repairs 11’9 -3/8” 
     No further reduction permitted 
   Min. low pitch setting at 42 in. sta.  21  
 2. 4 propeller governors 
  (a) Ham. Std. 4G8     26 lb (+277.0) 
  (b) Woodward WH44 or WH45 (Equivalent to Ham. Std. 4G8-P30M) 26 lb. (+277.0) 
  (c) Ham. Std. 5G8 (To be used on Wr ight 736C9HD1 engines only) 38 lb. (+273.0) 
 
Engines and Engine Accessories - Fuel and Oil Systems 
 
100. 4 engines 
  (a) P&W 2SD-G or R-2000-7  -2:1 pr opeller reduction gearing  6232 lb. (+275.3) 
   Fuel  100 min. grade aviation gasoline       and    (+305.1) 
   Limits 
  
HP 
 
RPM 
MP  
In. Hg 
 
ALT 
Low impeller gear ratio 7.15:1     
 Take-off (2 minutes)  1350 2700 50.0 - - - - 
 Maximum continuous 1100 2550 42.0 S.L. 
 Maximum continuous 1100 2550 41.0 7400’ 
High impeller gear ratio 8.47:1     
 Maximum continuous 1000 2550 42.0 10000’ 
 Maximum continuous 1000 2550 41.5 12400’ 
    (Straight line manifold pressu re variation with altitudes shown). 
    Placard required  See NOTE 2b 
 
  (b) P&W 2SD1G or R-2000  -9-2:1 propeller reduction gearing 6288 lb. (+275.3) 
   Fuel  100 min grade aviation gasoline       and    (+305.1) 
   Limits 
  
HP 
 
RPM 
MP  
In. Hg 
 
ALT 
Low impeller gear ratio 7.15:1     
 Takeoff (2 minutes) 1450 2700 50.0 - - - - 
 Maximum continuous 1100 2550 38.5 S.L. 
 Maximum continuous 1100 2550 36.5 8300’ 
High impeller gear ratio 9.52:1     
 Maximum continuous 1000 2550 39.0 10000’ 
 Maximum continuous 1000 2550 37.5 17700’ 
    (Straight line manifold pressu re variation with altitudes shown) 
    Placard required  See NOTE 2b 
 
  (c) P&W R-2000-11 - 2:1 propeller reduction gearing  6232 lb. (+275.3) 
   Fuel  100 min grade aviation gasoline         and  (+305.1) 
   Limits 
  
HP 
 
RPM 
MP  
In. Hg 
 
ALT 
Low impeller gear ratio 7.15:1     
 Takeoff (2 minutes) 1350 2700 46.0 - - - - 
 Maximum continuous 1100 2550 38.5 S.L. 
 Maximum continuous 1100 2550 36.5 8300’ 
High impeller gear ratio 9.52:1     
 Maximum continuous 1000 2550 39.0 10000’ 
 Maximum continuous 1000 2550 37.5 17700’ 
    (Straight line manifold pressure variation with altitudes shown) 
     Placard required  See NOTE 2b

(d) P&W 2SD13G or R-2000-11M2 - 2:1 propeller reduction gearing 6288 lb. (+275.3) 
   Fuel  100 min grade aviation gasoline         and  (+305.1) 
   Limits 
  
HP 
 
RPM 
MP  
In. Hg 
 
ALT 
Low impeller gear ratio 7.15:1     
Takeoff (2 minutes) 1450 2700 50.0 - -  - -  
Maximum continuous 1200 2550 42.0    S.L. 
Maximum continuous 1200 2550 40.5   5200’ 
High impeller gear ratio 9.52:1     
Maximum continuous 1100 2550 44.0   7000’ 
Maximum continuous 1100 2550 43.0 15000’ 
     (Straight line manifold pre ssure variation with altitudes shown) 
     Placard required  See NOTE 2b 
     Elevator Control Column Balance Weights required per NOTE 8. 
   
  (e) Wright 736C9HD1 - 16:9 propeller reduction gearing   5440 lb.  (+268.2) 
   Fuel  100 min grade aviation gasoline       and     (+290.8) 
   Limits  
  
HP 
 
RPM 
MP 
In. Hg 
 
ALT 
Low impeller gear ratio 7.21:1     
 Takeoff (2 minutes) 1425 2700 51.5 S.L. 
 Maximum continuous 1275 2500 46.5 S.L. 
 Maximum continuous 1275 2500 45.5 3500’ 
High impeller gear ratio 8.69:1     
 Maximum continuous 1125 2500 44.5 7800’ 
 Maximum continuous 1125 2500 44.5 10600’ 
     (Straight line manifold pre ssure variation with altitudes shown) 
     Placard required  See NOTE 2b 
       See NOTE 2(c) regarding removal of cruise restriction 
     Elevator Control Column Balance Weights required per NOTE 8. 
     See NOTE 11 regardi ng installation requirements. 
 
  (f) P&W D-5 or R-2000-7M2 - 2:1 prope ller reduction gearing 6300 lb. (+275.3) 
   Fuel   100 min grade aviation gasoline        and   (+305.1) 
   Limits  
  
HP 
 
RPM 
MP  
In. Hg 
 
ALT 
Low impeller gear ratio 7.15:1     
 Takeoff (2 minutes) 1450 2700 50.0 S.L. 
 Maximum continuous 1200 2550 42.5 S.L. 
 Maximum continuous 1200 2550 41.5 7000’ 
     (Straight line manifold pre ssure variation with altitudes shown.) 
     Placard required  See NOTE 2b 
     Elevator Column Balance Weights required per NOTE 8 
 
  (g) P & W D-3 -2:1 propeller reduction gearing    6340 lb. (+275.3) 
   Fuel   100 min grade aviation gasoline        and   (+305.1) 
   Limits 
 HP RPM MP in 
Hg 
ALT 
Low impeller gear ratio 7.15:1     
Takeoff (2 minutes) 1450 2700 50.0 S.L. 
Maximum continuous 1200 2550 42.0 S.L. 
Maximum continuous 1200 2550 40.5 5200’ 
     (Straight line manifold pre ssure variation with altitudes shown) 
     Placard required  See NOTE 2b 
     Elevator Column Balance Weights required per NOTE 8

A-762 11
101. (a) Dump valve installation (Dougl as Dwgs. 5326098, 5327000, 5327001 171 lb (+406.1) 
   5327006, 5327009, 5327014, 5327025, 5327027, 5327101) 
  (b) Dump valve installation (Douglas Dwg. 5326874)    88 lb (+394.8) 
  (c) Standpipe installation (Douglas Dwgs 5327101F, 5327006E)     2 lb  (+411.0) 
  (d) Sandpipe installation (Douglas Dwgs.  5327006E, 5327101F)  Delta     1 lb (+411.0) 
  (e) Dump valve installation (Douglas Dwgs. 5327000, 5327001, 5327006, and 5327027) 116 lb (+394.5) 
 
102. System fuel and oil.  See NOTE 1b for definition. 
  (a) 8 wing tanks (C54F-DC, C54G-DC, DC-4)   340 lb. (+360.7) 
  (b) 6 wing tanks (C54-DC, C54A-DC, C54B-DC, C54D-DC)  296 lb. (+354.7) 
  (c) 6 wing and 2 fuselage tanks (C54B-DC, C54D-DC)  328 lb. (+349.4) 
  (d) 4 wing tanks and nacelle oil (C54-DC, C54A-DC)  221 lb. (+344.9) 
  (e) 4 wing and 4 fuselage tanks (C54-DC, C54A-DC)  323 lb. (+344.2) 
  (f) 4 wing and 3 fuselage tanks (C54-DC, C54A-DC)  307 lb. (+344.6) 
  (g) 6 wing tanks (C54E-DC, C54G-DC, DC-4)   324 lb. (+358.7) 
  (h) Item 102(a), (b), (c), (e), (f) or (g) when installed less fuselage oil tank may be  
   reduced     -38 lb, (+333.1) 
 
119. Nacelle, cowling, contro ls, lines, etc., forward of firewall in  changing to  
  Wright 736C9HD1 installation     -411 lbs. 
 
120. Rework anti-drag ring seal ri ng in accordance with Douglas Dwg. 
  #2357103 (winterization item)     Neglect weight change 
   Engine winterization equipment may be  installed on the P & W 2SD-G (R-2000-7),  
   P & W 2SD1-G (R-2000-9), R-2000-11 and 2SD13G engines only.  When  
   Item 120 is installed, the following placard must be suitably placed on the  
   instrument panel in full view  of the pilot: 
   “Engine winterization baffles inst alled must be changed when seasonal 
   temperatures exceed 80 F. 
 
Landing Gear 
200. (a) 4 Main Wheel 14-ply rating tires, 15.50-20, Type  III. (Inflation pressure 90 psi) 476 lbs. (+427.8) 
  (b) 4 Main Wheel 12-ply rating tires, 15.50-20, Type III. (Infl ation pressure 90 psi)               (+427.8) 
 
201. 4 Main Wheel tubes, 15.50-20, regular      70 lbs. (+427.8) 
 
202. Nose wheel tire, 44”, Type I 
  (a) 10 ply rating tire (10 ply rayon)   (Inflation pressure 60 psi)  102 lbs.(+100.5) 
  (b) 12 ply rating tire   (Inflation pressure 60 psi)     93 lbs. (+100.5) 
 
203. Nose wheel tube, 44”, regular       15 lbs. (+100.5) 
 
204. 4 Main Wheel - brake assemblies, 17.00-20, Type III 
  (a) Goodyear Model 20DHBM    852 lbs. (+427.8) 
   Wheel Assembly #530402-M 
   Brake Assembly #511064-M 
  (b) Goodrich Model 1751M     664 lbs. (+427.8) 
   Wheel Assembly #H-3-582-M-1 
   Brake Assembly #H-2-488-1 
   (This installation requires replacement of the brake deboosters in accordance  
   with Goodrich Dwg. H-99-1073 or equiva lent, and is eligible for a maximum  
   takeoff weight of 63,000 lbs.) 
  (c) Goodyear Model L20HBMF    658 lbs. (+427.8) 
   Wheel Assembly #9540049 
   Brake Assembly #9540039 
   (Accomplish this installation in accordance with Goodyear Instruction  
   “Wheel and Brake Changeover on DC-4 Aircraft to the 
   Goodyear Single Disc 1700-20 PD297.”  Goodyear Service 
   Letter DC4-11 has been approved rega rding reworked discs in this brake.)

205. Nose Wheel, 44” Type I 
  Goodyear Model 44SC, Assembly #530339-M     62 lbs. (+100.5) 
 
Electrical and Radio Equipment 
(See approved weight and balance report for each aircraft.) 
 
Interior Equipment 
400. Approved Airplane Flight Manual (Airpl ane Operating Manual is the equivalent). 
  (The manual may be carried as part of or  bound with, the operator’s “Approved Operations  
  Manual”, but must  remain in the airplane and must retain its identity as an individual manual). 
401. Emergency ladder, (Require d for passenger operation only) 
   Suitable evacuation chute installati ons are an acceptable substitute for the  
   emergency ladder installations. 
402. Automatic Pilot: 
  (1) Servo stall forces measured at the pilots controls: 
   Elevator 55 to 60 lbs. 
   Aileron 55 to 60 lbs. 
   Rudder 100 to 135 lbs. 
  (2) When using auto pilot in cruise confi gurations, minimum terrain clearance is 500 feet.   
   When using autopilot during approach, mi nimum altitude is 200 feet, pilots seat belt  
   fastened and hand on control wheel.  (M inimum altitude for each case does not override 
   any higher minimum operational altitudes.) 
   (a) Jack  & Heintz Type A3A   116 lbs. (+132.6) 
    (Servo Unit Model Nos. (2) C11-D1-B; (1) C15-D1-B) 
   (b) Sperry Type A3     120 lbs. (+126.2) 
    (Servo Unit Model Nos. (2) C11-D1-B; (1) C15-D1-B) 
   (c) Sperry A-12     245.5 lbs.(+428.2) 
    (Servos, 3 P/N 661634 and 1 P/N 661202) 
    (Douglas Dwg. No. 4350746, UAL Dwg. Nos. 15F-309.  15F-311 and 9F-413) 
 
423. Windshield Wipers 
  (a) 2 Marquette Metal Products Mode l 50V28       6.6 lbs. (+90.0) 
  (b) 2 Marquette Metal Products Mode l 50V39       6.9 lbs. (+90.0) 
 
De-icing Equipment 
500. Wing and Tail Surface de-icer boots 
  (Other combinations of long and short chor d boots, listed below, may be used providing  
  they are suitably installed with respect to plumbing and attachment details). 
  (a) Long Chord     217 lbs. (+539.6) 
   Wing (Goodrich Model 5-294-1 thru -4) 
   Stabilizer (Goodrich Model 5-294-5) 
   Fin (Goodrich Model 2-294-6) 
  (b) Combination Long and Short Chord   207 lbs. (+523.7) 
   Wing (Goodrich Model 11-661-7 and -8; 12-661-9; 5-294-4) 
   Stabilizer (Goodrich Model 5-294-5)  
   Fin (Goodrich Model 2-294-6) 
  (c) Short Chord     211 lbs. (+523.5) 
   Wing (Goodrich 11-661-7 and -8; 12-661-9 and -10) 
   Stabilizer (Goodrich 12-661-11) 
   Fin (Goodrich 11-661-12) 
  (d) Pitot Mast (8-294) 
 
503. Propeller De-Icer Fluid Feed Strips (Goodrich 37572) and feed rings      8 lbs. (+262.0) 
  (Goodrich 36889).  Strips must not ex tend beyond prop.  50 inch station. 
  No reduction in performance or ceilings.    
 
Miscellaneous (not listed above) 
(See approved weight and balance report for each aircraft.) 
612. Control column balance weights (4)     78 lbs.(+98.0) 
  See NOTE 8 regarding extension of rear  C.G. limit when this item is installed.

A-762 13
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 operato rs having an approved weight control system). 
    Manufacturer’s Master Equipment List cont ains list of approved equipment in addition to 
    equipment listed in this specification. 
 
   (b) “System Fuel and Oil,” which must be included in the empty weight, is that amount required to fill  
    both systems and the tanks up to the tank outlets to the engines, when the airplane is in the level 
    attitude.  The propeller feathering oil is not cons idered usable oil, and is included in the “System 
    Fuel and Oil.”  The nacelle oil tank capacities shown in this specification include only the usable 
    oil for which the tanks are to be placarded. 
 
   (c) For passenger and extra crew member seat lo cations, see approved weight and balance report for the 
    particular model airplane.  Lounges and lavatori es should be placarded for the capacities specified in the 
    approved loading schedule. 
 
   (d) The airplane must always be loaded with in the C.G. limits specified, accounting for crew and 
    passenger movement and use of fuel and oil.  Retraction of the landing gear changes the airplane 
    balancing moment by -193,400 inch  lbs. and moves the C.G. forward. 
 
NOTE 2 The following placards shall be placed on the instrument panel in full view of the pilot: 
   (a) “This airplane shall be operated in accord ance with the FAA Approved Airplane Flight Manual.” 
    (FAA Approved Operating Ma nual equivalent.)  (All Models) 
 
   (b) With item 100(a), (b), (c), (d), (f) or (g) engines:  “Continuous operation of engines between  
    2310-2510 rpm prohibited.” 
    With item 1(a) propellers and 100(a) , (b), (c), (d), (f), or (g) engines: 
    “Avoid continuous operation between 1550 and 1750 rpm and between 2310 and 2510 rpm. 
    During ground running, avoid operation betw een 1550 and 1800 rpm when the blades are off 
    the low pitch stops.” 
 
   (c) With item 100(e) engines: 
    “Continuous operation of engi nes between 2050-2200 is prohibited. 
    Maximum cruise rpm 2050.” 
    When wing spars have been reinforced in  accordance with Chicago & Southern Dwg. B4-1452, 
    the “Maximum cruise rpm 2050” may be deleted from the placard. 
 
   (d) On all models with outer wi ng tanks installed except model C54-DC: 
    “Do not land with more than 395 gallons of fuel in each outboard main tank and outboard 
    auxiliary tank combined and with not more than & total of 790 gallons of fuel in the main 
    tanks and outboard auxiliary tank in either wing.” 
 
   (e) On model C54-DC with outer wing tanks installed: 
    “Do not land with more than 358 gallons of fuel in each outboard main tank and outboard 
    auxiliary tank combined and with not more than a total of 715 gallons of fuel in the main 
    tanks and auxiliary tank in either wing. 
 
NOTE 3 (a) Fuel Dumping. Fuel dump valves (Item 101)  must be installed for operation of the airplane 
    at weights in excess of maximum landing weight as indicated in Table “A” of NOTE 9.  
    Limitations to be observed during the dumping of fuel and which should be contained in the CAA 
    Approved Airplane Flight Manual are covere d in Subparagraphs (b), (c), and (d) below. 
 
   (b) Fuel shall not be dumped except when flaps and landing gear are retracted.  After fuel has been 
    dumped, flight shall not be continued at a speed greater than 193 mph .  True indicated on the  
    Model C54-DC and 209 mph Tr ue Indicated on all other models.

NOTE 3  (cont’d) (c) On all Model C54B-DC, C54D-DC, C54E-DC, C54G-DC, DC-4, and C54-DC or C54A-DC  
    aircraft with outer wing tanks installed, th at have only two dump chutes which are connected to 
    the outboard main and outboard auxiliary tanks  (one dump chute each side of the centerline), it 
    is not possible to dump sufficient fuel to redu ce the gross weight for landing when the aircraft is 
    loaded to its maximum permissible “zero fu el weight” and only the minimum amount of fuel  
    required by the Speed and Load Factor Limita tions Chart is loaded in Accordance with NOTE 10. 
    Therefore, the maximum “zero fuel weight of the aircraft must be reduced sufficiently to insure that  
    there will be enough fuel in the outboard ma in and outboard auxiliary tanks for dumping down to 
    the approved landing weight, accounting for the amount of fuel remaining in the tanks after  
    dumping. 
 
   (d) When dump valves are insta lled (Item 101), the amount of fuel remaining in the fuel tanks after  
    dumping is as follows: 
    Outboard Main   70 gallons each 
    Inboard Main    70 gallons each 
    Outboard Auxiliary  53 gallons each 
    Inboard Auxiliary (if installed)  91 gallons each 
 
NOTE 4 Prior to certification as a civil aircraft, the requi rements for certification as outlined in the following listed 
   reports for the particular model must be complied with: 
    C54-DC    Douglas Report No. SM11139 
    C54A-DC Douglas Report No. SM11157 
    C54B-DC Douglas Report No. SM11158 
    C54D-DC Douglas Report No. SM11159 
    C54E-DC Douglas Report No. SM11147 
    C54G-DC Douglas Report No. SM11160 
   Because the requirements  for original certificati on are different for each model, the original model  
   designation should be retained re gardless of whether the engine is the same as originally installed or 
   whether a different engine is installed.  (See “Optional Equipment” items for each model for alternate 
   engine installations.) 
 
NOTE 5 Passenger seats and safety belt in stallations other than originally provided by the manufacturer must be 
   of an approved type or shown to meet the strength requirement of CAR 4. 
 
NOTE 6   Because two emergency exits are not available when  three or four fuselage tanks are installed , only 22  
    passengers, including crew members, may be carri ed in the passenger compartment.  When tanks are 
    removed, or when the two fo rward tanks are installed and the forward cabin bulkhead is moved forward 
    to clear the emergency exits, the capacity of the cabin may be increased to that corresponding to the  
    number of seats installed. 
 
NOTE 7  When fuselage oil tanks are removed, the airpla ne must be placarded to avoid carrying more than 2400  
    gallons of fuel when the nacelle oil tanks are f illed to their total usable capacity of 80 gallons, thereby 
    insuring a fuel oil ratio of not over 30 to 1.  Th e auxiliary fuel tanks should be placarded for the quantity 
    of gasoline not to exceed the difference between 2400 gallons and the total capacity of the main fuel  
    tanks.  On aircraft which have only the four center wing integral tanks and with not more than one 
    fuselage fuel tank installed, the fuselage o il tank may be removed and the above placard will not be 
    necessary. 
 
NOTE 8    When Elevator Control Column Balance We ights (Item 612) are installed in accordance with the 
    Douglas or Drawings listed be low, the rear C.G. may be extended to (407.6) with gear retracted  
    for enroute operation: 
     All C54-DC Series  Dwg. 5327119 
           DC -4  Dwg. 5102774-503 
     On aircraft having engines of more th an 1100 maximum continuous horsepower installed the 
     Control Column Balance Wei ghts (Item 612) must be installed. 
 
NOTE 9 Table “A” below lists the maximum landing and ta ke-off weights for the various airplane and engine 
   installations covered by this specification.  When  dump valves are required for the higher take-off weights 
   indicated in  Table “A”, standpipes must also be  installed in the dump valve system in accordance with 
   Douglas Dwgs. Nos. 5327006, Change “E”,  and 5327101, Change “F”.  (See Item 101(c)).

A-762 15
NOTE 9 Table “B” lists the airs peed limits at which the different models may be operated for the various maximum  
  (cont’d) weights and fuel and nacelle oil load conditions.  For airspeed limits at other weight and fuel and nacelle 
   oil combinations, see the “Speed and Load Factor Limitations” chart in the approved Flight Manual for the 
   particular model airplane in question. 
 
TABLE “A” (See NOTE 9 for description of table) 
 
MAXIMUM WEIGHTS 
  C54-DC C54A-DC C54B-DC; 
 
Engine 
Installation 
 
 
Conditions 
 
Without Outer 
Wing Tanks 
Outer Wing 
Tanks Installed 
(1) 
 
Without Outer 
Wing Tanks 
Outer Wing 
Tanks Installed 
(1) 
C54D-DC;  
C54E-DC;  
C54G-DC; DC-4 
P&W  
2 SD-G 
 
or 
R-2000-7 
Landing 
 
 
Takeoff 
 
 
 
61,100 
62,000 (4) 
 
62,000 (3) 
 
 
 
 
59,200 (8) 
68,000 (2) 
 
 
 
61,100 
63,000 (4) 
63,500 (4) (6) 
63,000 (3) 
65,000 (3) (4)   
  (6) 
 
61,000 (5) 
63,500 (4)(5) 
 
64,150 (3) 
66,670 (3)(4) 
70,700 (2) 
71,800 (2)(7) 
61,000 (5) 
63,500(4)(5) 
64,150 (3) 
66,670 (3)(4) 
70,700 (2) 
71,800 (2)(7) 
P&W  
2SD1G 
or 
R-2000-9 
Landing 
 
Take-off 
62,000 
 
62,000 
59,200 (8) 
68,000 (2) 
63,000 
63,500 (6) 
63,000 
65,000 (3)(6) 
63,500 (5) 
 
66,670 (3) 
71,800(2) 
63,500 (5) 
66,670 (3) 
71,800 (2) 
P&W 
 
 
R-2000-11 
Landing 
 
Take-off 
61,100 
62,000 (4) 
 
62,000 (3) 
 
59,200 (8) 
68,000 (2) 
61,100 
63,000 (4) 
63,500 (4)(6) 
63,000 (3) 
65,000 (3) (4)  
  (6) 
61,100 (5) 
63,500 (4)(5) 
64,150 (3) 
66,670 (3)(4) 
70,700 (2) 
71,800 (2)(7) 
61,100 (5) 
63,500 (4)(5) 
64,150 (3) 
66,670 (3)(4) 
70,700 (2) 
71,800 (2)(7) 
P&W 
2SD13G, 
D-3 or  
D-5 
Landing 
 
Take-off 
62,000 
 
62,000 
59,200 (8) 
 
68,000 (2) 
63,000 
63,500 (6) 
63,000 
65,000 (3)(6) 
63,500 (5) 
64,170 (5)(9) 
66,670 (3) 
73,000 (2) 
73,800 (2)(9) 
63,500 (5) 
64,170 (5)(9) 
66,670 (3) 
73,000 (2) 
73,800 (2)(9) 
Wright 
736C9HD1 
Landing 
 
Take-off 
61,600 
62,000 (3) 
 61,600 
63,000 (3) 
61,600 (5) 
63,500 (4)(5) 
64,680 (3) 
66,670 (3)(4) 
70,000 (2) 
61,600 (5) 
63,500 (4)(5) 
64,680 (3) 
66,670 (3)(4) 
70,000 (2) 
(1)  These weights permitted only when outer  wing panels incorporating integral fuel tanks are installed and the fuel system  
  revised to be equivalent to that installed in the Model C54B-DC.  Any deviations from the C54B-DC system must be 
  brought to the attention of the Aircraft Engineering Division, Civil Aeronautics Administration, for approval. 
(2) Dump valves required.  See NOTE 3B, 3C, and 3E for details. 
(3) Dump valves not required. 
(4) These weights are permitted when a 35 degree landing flap se tting is used and the aircraft is operated in accordance  
  with Appendix I of the approved Flight Manual whic h covers the performance relative to this flap setting. 
(5) See NOTE 2(d) for required placar d with outer wing tanks installed. 
(6)  These weights permitted only when aircraft rewo rked in accordance with Douglas Dwgs. 5395880 and 5395881 and 
  operated in accordance with “A pproved Flight Manual” revisions. 
(7) Applicable with 5 degree take-off flap when pertinent revisions dated 5-15-51 are contained in CAA Approved Flight  
  Manual, or also applicable for sea level operations when airplane is in the configuration specified in Seaboard &  
  Western Airlines’ Report No. 2x1 and th e Approved Airplane Flight Manual includes the revision material appended to  
  that  report (CAA Approved 7-25-50). 
(8) See NOTE 2(e) for required placar d with outer wing tanks installed. 
(9)  Operation at the increased landing and take-off weights perm issible when the Approved Flight Manual has been revised 
  in accordance with Seaboard and We stern Airlines Report No. 2x-2.

TABLE “B” See NOTE 9 for description and NOTE 10 for additional limitations. 
 
MODEL C-54-DC See Fig. 1, Curve No. 1, of approved Flight Manual for “Speed and Load Factor Limitations.”  Page 5 
Revised November 9,  1956. 
Fuel Wt. Cond. 
Airspeed Limits 
Zero Fuel & Nacelle Oil 
52,400 lbs. Max Wt. 
  9,600 lbs Fuel & Nacelle Oil 
62,000 lbs Max. Wt. 
 
VO (Max Cruising) 
VP (Maneuvering) 
VNE (Never Exceed) 
VF (Flaps Down)   20 
                              30 
                  40 and up 
193 mph (168 knots) True Ind 
175 mph (152 knots) True Ind 
231 mph (201 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
221 mph (192 knots) True Ind 
157 mph (137 knots) True Ind 
265 mph (231 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
 
Model C-54A-DC (Without Outer Wing Tanks).  See Fig. 1, Cu rve No. 2, of Approved Flight Manual for “Speed & Load 
Factor Limitations”. 
Fuel Wt. Cond. 
Airspeed Limits 
Zero Fuel & Nacelle Oil 
51,200 lbs. Max. Wt. 
Zero Fuel & Nacelle Oil 
58,000 lbs. Max. Wt. 
  6,900 lbs. Fuel & Nacelle Oil 
63,000 lbs. Max Wt. 
VO   (Max. Cruising) 
VP   (Maneuvering) 
VNE (Never Exceed) 
VF   (Flaps Down)   20 
                                30 
                   40 and up 
250 mph (218 knots) True Ind 
175 mph (152 knots) True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind. 
209 mph (182 knots) True Ind 
170 mph (148 knots) True Ind 
250 mph (218 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
224 mph (195 knots) True Ind 
176 mph (153 knots) True Ind 
269 mph (234 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
Model C-54A-DC (Without Outer Wing Tanks).  (When modified in accordance with Douglas Dwgs. 5395880 and 
5395881).  See Fig. 1, Curve No. 9, of Approved Flight Manual for “Speed and Load Factor Limitations”. 
Fuel Wt. Cond. 
Airspeed Limits 
Zero Fuel & Nacelle Oil 
51,200 lbs. Max. Wt. 
Zero Fuel & Nacelle Oil 
58,000 lbs. Max. Wt. 
  9,000 lbs. Fuel & Nacelle Oil 
65,000 lbs. Max. Wt. 
VO  (Max. Cruising) 
VP  (Maneuvering) 
VNE (Never Exceed) 
VF  (Flaps Down)   20 
                               30 
                     40 and up 
250 mph (218 knots) True Ind. 
175 mph (152 knots) True Ind. 
300 mph (261 knots) True Ind. 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
209 mph (182 knots) True Ind. 
170 mph (148 knots) True Ind 
250 mph (218 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
232 mph (202 knots) True Ind 
179 mph (156 knots) True Ind 
278 mph (242 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
Model C54B-DC, C54D-DC and C54A-DC (With Outer Wing Tanks).   See Fig. 1, Curve No. 3, of Approved Flight Manual 
for “Speed and Load Factor Limitations”. 
Fuel Wt. Cond. 
Airspeed Limits 
Zero Fuel and Nacelle Oil 
51,200 lbs Max Wt 
Zero Fuel and Nacelle Oil 
58,000 lbs. Max. Wt. 
15,000 lbs. Fuel & Nacelle Oil 
73,000 lbs. Max Wt. 
VO  (Max. Cruising) 
VP  (Maneuvering) 
VNE (Never Exceed) 
VF  (Flaps Down)    20 
                                30 
                    40 and up 
250 mph (218 knots) True Ind. 
175 mph (152 knots) True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
209 mph (182 knots) True Ind 
170 mph (148 knots) True Ind 
250 mph (218 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots)  True Ind 
250 mph (218 knots) True Ind 
188 mph (164 knots) True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
Model C54B-DC, C54D-DC, C54E-DC and C54A-DC (With Outer Wing Tanks) (When modified in accordance with 
Douglas Service Bulletin DC-4 No. 44).  See Fig. 1, Curve No. 4, of Approved Flight Manual for “Speed and Load 
Factor Limitations”. 
Fuel Wt. Cond. 
Airspeed Limits 
Zero Fuel & Nacelle Oil  
51,200 lbs. Max. Wt. 
Zero Fuel & Nacelle Oil 
59,000 lbs. Max. Wt. 
14,000 lbs. Fuel & Nacelle Oil 
73,000 lbs. Max. Wt. 
VO  (Max. Cruising) 
VP  (Maneuvering) 
VNE (Never Exceed) 
VF  (Flaps Down)    20 
                                30 
                    40 and up  
250 mph (218 knots) True Ind 
175 mph (152 knots) True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
212 mph (181 knots) True Ind 
170 mph (148 knots) True Ind 
254 mph (221 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
250 mph (218 knots) True Ind 
188 mph (164 knots) True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
Model C54G-DC and DC-4 (1).  See Fig. 1, Curve No. 5,  of Approved Flight Manual for “Speed and Load Factor 
Limitations”. 
Fuel Wt. Cond. 
Airspeed Limits 
Zero Fuel & Nacelle Oil 
55,500 lbs. Max. Wt. 
Zero Fuel & Nacelle Oil 
60,700 lbs. Max. Wt. 
12,300 lbs. Fuel & Nacelle Oil 
73,000 lbs. Max. Wt. 
VO  (Max. Cruising) 
VP  (Maneuvering) 
VNE (Never Exceed) 
VF  (Flaps Down)    20 
                                30 
                   40 and up 
250 mph (218 knots) True Ind 
178 mph (155 knots) True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
217 mph (189 knots) True Ind 
174 mph (151 knots) True Ind 
260 mph (226 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
250 mph (218 knots) True Ind 
191 mph (166 knots)  True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind

A-762 17
  Table “B” See NOTE 9 for descrip tion and NOTE 10 for addition limitations 
  Applies to the models as indicated which incorporate a Fuel Dump Chute installation having only two dump chutes and  
   when P & W 2SD13G or D-5 engines are installed. 
 
Model C54B-DC, C54D-DC, C54E-DC and C54A-DC (With Outer Wing Tanks).  See Fig. 1, Curve No. 6, 
of Approved Flight Manual for “Speed and Load Factor Limitations”, pages 5 through 6b dated 
October 6,  1948. 
Fuel , Oil Wt Cond 
Airspeed Limits 
Zero Fuel & Nacelle Oil 
51,200 lbs. Max. Wt. 
Zero Fuel & Nacelle Oil 
57,000 Max. Wt. 
16,000 lbs. Fuel & Nacelle Oil 
73,000 lbs. Max. Wt. 
VO  (Max. Cruising) 
VP  (Maneuvering) 
VNE (Never Exceed) 
VF   (Flaps Down)      20 
                                   30  
                          40 and up 
250 mph (218 knots) True Ind 
175 mph (152 knots) True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
214 mph (186 knots) True Ind 
170 mph (148 knots) True Ind 
257 mph (224 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
250 mph (218 knots)  True Ind 
188 mph (164 knots)  True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots)  True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
Model C54B-DC, C54D-DC, C54E-DC and C54A-D C (With Outer Wing Tanks) (When modified in 
accordance with Douglas Service Bulletin DC-4 No. 44.)  See Fig. 1, Curve No. 7 of Approved 
Flight Manual for “Speed and Load Factor Limitations,” pages 5 through 6b dated April 6, 1951. 
Fuel, Oil Wt Cond. 
Airspeed Limits 
Zero Fuel & Nacelle Oil 
51,200 lbs. Max. Wt. 
Zero Fuel & Nacelle Oil 
59,000 lbs. Max. Wt. 
14,000 lbs. Fuel & Nacelle Oil 
73,000 lbs. Max. Wt. 
VO  (Max. Cruising) 
VP  (Maneuvering) 
VNE (Never Exceed) 
VF  (Flaps Down)      20 
                                  30  
                        40 and up 
250 mph (218 knots) True Ind 
175 mph (152 knots) True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
213 mph (185 knots) True Ind 
170 mph (148 knots) True Ind 
256 mph (223 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
250 mph (218 knots) True Ind 
188 mph (164 knots) True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
Model C54B-DC, C54D-DC, C54E-DC and C54A-DC (With Outer Wing Tanks)  (When modified in 
accordance with Part B of Douglas Service Bulletin DC-4 No. 44) .  See Fig. 1, Curve No. 8 of 
Approved Flight Manual for “Speed and Load Factor Limitations”, pages 5 through 6b, dated 
October 6.  1948. 
Fuel, Oil Wt Cond 
Airspeed Limits 
Zero Fuel & Nacelle Oil 
51,200 lbs. Max. Wt. 
Zero Fuel & Nacelle Oil 
58,000 lbs. Max. Wt. 
15,000 lbs. Fuel & Nacelle Oil 
73,000 lbs. Max. Wt. 
VC  (Max. Cruising) 
VP  (Maneuvering) 
VNE (Never Exceed) 
VF  (Flaps Down)      20 
                                  30  
                      40 and up 
250 mph (218 knots) True Ind 
175 mph (152 knots) True Ind 
300 mph (261 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
209 mph (182 knots) True Ind 
170 mph (148 knots) True Ind 
250 mph (218 knots)  True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
250 mph (218 knots) True Ind 
188 mph (164 knots) True Ind 
300 mph (261 knots)  True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
Model *C54-DC (With Outer Wing Tanks and 2 Fuel Dump  Chute System).  See Fig. 1, Curve X, of CAA 
Approved Airplane Flight Manual revision dated November 28,  1951.  
Fuel, Oil Wt Cond 
Airspeed Limits 
Zero Fuel & Nacelle Oil 
53,400 lbs. Max. Wt. 
  7,500 lbs. Fuel & Nacelle Oil 
59,200 lbs. Max. Wt. 
17,300 lbs. Fuel & Nacelle Oil 
68,000 lbs. Max. Wt. 
VC  (Max. Cruising) 
VP  (Maneuvering) 
VNE  (Never Exceed) 
VF  (Flaps Down)       20 
                                   30  
                       40 and up 
195 mph (168 knots) True Ind 
175 mph (152 knots) True Ind 
231 mph (201 knots) True Ind 
202 mph (176 knots)  True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
212 mph (184 knots) True Ind 
175 mph (152 knots) True Ind 
254 mph (220 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
241 mph (210 knots) True Ind 
180 mph (156 knots) True Ind 
289 mph (251 knots) True Ind 
202 mph (176 knots) True Ind 
158 mph (137 knots) True Ind 
154 mph (134 knots) True Ind 
 
*The landing gear on the Model DC-4 may be extended at a maximum speed of 180 mph True Ind.  On all other models, the 
maximum speed at which the gear may be extended is 144 mph True Ind. unless the nose wheel doors have been modified in 
accordance with Douglas Service Bulletin No. C-54-288.  After modification, the maximum speed at which the landing gear may 
be extended can be increased to 180 mph True Ind.

(1) All models C54G-DC and DC-4 aircra ft originally incorporated outer wing panels, P/N 5241819-500, -501, -502, -503,  
  -506 or -507.  Replacement outer wing panels produced by th e manufacturer, that are equivalent to those originally  
  installed on C54G-DC and DC-4 aircraft are assigned a 1400 series dash number  of the basic assembly #5241819.  If 
  other outer wing panels of another dash number or of a nother part number are installed, the maximum zero fuel and  
  nacelle oil-gross weight must be reduced from 60,700 to 59,000 lbs. 
 
NOTE 10 All DC-4 and C54-DC Series aircraft must be operate d in accordance with the approved “Speed and Load Factor  
   Limitations Chart”, shown in the pe rtinent approved Flight Manual referred to in Table “B” for the various models. 
   The “Speed and Load Factor Lim itations Chart” indicates the maximum take-off weight and corresponding speed at  
   which the aircraft may be operated in  flight depending upon the amount of fuel and oil in the wing prior to take-off.   
   The weight of the aircraft as loaded less fuel and n acelle oil shall not exceed the “Zero Fuel and Nacelle Oil Gross 
   Weights” shown on the pertinent “Sp eed and Load Factor Limitations Chart.”  Fuel must be loaded equally in the 
   main tanks and consumed equally.  If the aircraft has 6 or 8 wing tanks, the main tanks must be filled first before  
   fuel is loaded in the auxiliary tanks .  In the case of the eight wing tank aircraft the outboard auxiliary tanks must be  
   filled after filling the main tanks, befo re any fuel is loaded in the inboard auxiliary tanks.  Take-off and landing must  
   be made on the main tanks.  If fuel has been loaded in th e auxiliary tanks, it must be consumed after take-off prior to  
   using the fuel in the main tanks. 
 
   In the eight wing tank airplane, it is al so possible to load fuel as follows:   
   (a) Load fuel in the inboard and outboard auxiliary fuel ta nks equally or load the inboard tanks first, after the main  
    tanks have been filled, instead of loading fu el in the outboard auxiliary tanks as specified above. 
   (b)  Fuel may be loaded in the inboard auxiliary tanks before the main tanks and outboard auxiliary tanks; in this  
    condition, the remaining fuel must be loaded in the main tanks first and then the outboard auxiliary tanks.  If  
    either of these alternate procedures  is used, the weight of all fuel loaded in the inboard auxiliary tanks must be  
    considered as fuselage weight, and only that fuel lo aded in the outboard auxiliary and the main tanks may be  
    considered as fuel weight in the wing for operation of the airplane in accordance with the “Speed and Load  
    Factor Limitations Chart.”  Fuel must be used from the outboard auxiliary tanks before the fuel is consumed  
    from the main tanks except for take-off and landing, in which case fuel must be used from the main tanks. 
 
   On aircraft incorporating two fuel dump chutes, one on eight wing and attached to the outboard main and auxiliary 
   fuel tanks, it is impossible to dump sufficient fuel to reduce the weight down to the maximum landing weight when  
   fuel is loaded in accord ance with the procedures outlined above.  Therefore, on aircraft incorporating two fuel dump 
   chutes and P&W 2SD13G or D-5 engines, the fuel lo ading procedures and “Speed and Load Factor Limitations” 
   referred to in Table “B” above should be followed.  On all other aircraft incorporating two fuel dump chutes and  
   other engine installations, it will be necessary to reduce the maximum zero fuel and nacelle oil-gross weight to such  
   a point that it will be possible to reduce the weight by  dumping to the maximum approved for landing when fuel is  
   loaded in accordance with paragraph 1 and 2 above. 
 
NOTE 11 The installation of Wright 736C9HD1 engine power engi ne involves all components forward of the firewall and is 
   covered by Rohr Aircraft Dwg. No. 1-622-001, “installati on Power Plant.”  To complete the installation of the  
   Wright 736C9HD1 engine, the aircraft must also be  modified in accordance with the following Chicago and  
   Southern Dwgs.: 
    54-02-E-3024, “Control Pedestal Rework” 
    54-02-E-4014, “Panel Assembly - Pilots Switch” 
    54-02-E-4015, “Name Plat es - Pilots Switch Panel” 
    54-02-E-4017, “Pilots Overhead Instrument Panel Assembly” 
    54-02-E-4042, “Switch Panel Inst. & Asse mbly Prop. Synchronizer Pilots’ Pedestal” 
    54-02-E-4050, “Elec. Provisions Inst. -  Nacelle Firewall.” 
    54-02-E-5019, “Synchronizer Inst. - Propellers” 
 
NOTE 12 Deleted - October 15,  1951. 
 
NOTE 13 (a) Ferry permits may be issued to all model C54 Series and DC-4 aircraft on which one engine is inoperative with  
    its propeller removed or feathered under the following conditions: 
    (1) Operation of aircraft shall be in accordance with pertinent limitations contained in the applicable  
      portion of the CAA Approved Airplane Fli ght Manual, pertinent CAA approved appendices submitted 
      by Delta Airlines, and existing instructions. 
    (2) Maximum take-off weight 51,000 lbs. (except when limited by runway lengths specified in manual). 
    (3) C.G. range:  16% MAC (381.4) to 32% MAC (407.6)

A-762 19
NOTE 13 (b) Ferry permits may also be issued to Model C54 se ries and DC-4 aircraft equipped with P & W  2SD13G or  
  (cont’d)  R-2000-9 engines on which one  engine is inoperative with its propeller removed or feathered under the  
    following conditions: 
    (1) Operation of aircraft shall be in accordance with pertinent limitations contained in the applicable 
      portions of the CAA Approved Airplane F light Manual, pertinent CAA approved appendix submitted 
      by American Airlines or KLM, and existing instructions. 
    (2) Maximum take-off weight 55,700 lbs. (except when limited by runway lengths specified in manual). 
    (3) C.G. Range:  16% MAC (381.4) to 24.8% MAC (395.8) 
 
NOTE 14 In accordance with the agreement be tween the Department of Defense and the Civil Aeronautics Board, all air  
   carrier operators utilizing aircraft which have been m odified under the Civil Reserve Air Fleet Program, Part I,  
   Phase II, may deduct the added weight of the military  modification up to a maximum of 50 pounds for each aircraft 
   so modified.   
 
.....END.....
```

## ADs (55, first 50, in force first)

- [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026
- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2011-12-01](https://openairdocs.org/ad/2011-12-01): Equipment/Furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 268 more. Effective Aug 1, 2011
- [AD 2000-04-03](https://openairdocs.org/ad/2000-04-03): Airframe Pneumatic Deicing Boots · Boeing DC-4, DC3-G102, DC3-G102A and 12 more. Effective Mar 28, 2000
- [AD 98-04-35](https://openairdocs.org/ad/98-04-35): AFM - Limitations Section - Icing · Boeing DC-4, DC3-G102, DC3-G102A and 12 more. Effective Mar 25, 1998
- [AD 93-14-12](https://openairdocs.org/ad/93-14-12): Crewmember Protective Breathing Equipment Units · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 201 more. Effective Sep 2, 1993
- [AD 85-23-04](https://openairdocs.org/ad/85-23-04): LH/RH Elevator Trim Tab Inspection · Boeing C54-DC, C54A-DC, C54B-DC and 4 more. Effective Dec 5, 1985
- [AD 47-02-03](https://openairdocs.org/ad/47-02-03): Accumulator · Boeing C54-DC, C54A-DC, C54B-DC and 4 more. Effective Mar 27, 1980
- [AD 77-10-01](https://openairdocs.org/ad/77-10-01): Fire Resistant Prop Feathering System · Boeing C54-DC, C54A-DC, C54B-DC and 4 more. Effective Jun 16, 1977
- [AD 62-26-01](https://openairdocs.org/ad/62-26-01): Operating Restrictions · Boeing C54-DC and DC-4. Effective Jan 8, 1963
- [AD 46-11-02](https://openairdocs.org/ad/46-11-02): Copilot Oxygen Regulator · Boeing C54-DC, C54A-DC, C54B-DC and 3 more
- [AD 46-11-03](https://openairdocs.org/ad/46-11-03): Landing Gear Door Stud · Boeing C54-DC, C54A-DC, C54B-DC and 1 more
- [AD 46-24-02](https://openairdocs.org/ad/46-24-02): Magneto Wires · Boeing C54-DC, C54A-DC, C54B-DC and 3 more
- [AD 46-27-01](https://openairdocs.org/ad/46-27-01): Spar Webs · Boeing C54-DC, C54A-DC, C54B-DC and 3 more
- [AD 46-27-02](https://openairdocs.org/ad/46-27-02): Nose Wheel Brace Strut Collar · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 46-39-03](https://openairdocs.org/ad/46-39-03): Magneto Wires · Boeing C54-DC, C54A-DC, C54B-DC and 3 more
- [AD 46-39-04](https://openairdocs.org/ad/46-39-04): Fuel Tank Selector and Crossfeed Valves · Boeing C54-DC, C54A-DC, C54B-DC and 3 more
- [AD 46-39-05](https://openairdocs.org/ad/46-39-05): Main Fuel Line Supporting Brackets · Boeing C54-DC, C54A-DC, C54B-DC and 3 more
- [AD 47-02-01](https://openairdocs.org/ad/47-02-01): Exhaust Collector Rings · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-02-02](https://openairdocs.org/ad/47-02-02): Vertical Stabilizer Forward Attach Fitting · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-02-04](https://openairdocs.org/ad/47-02-04): Engine Primer Solenoid · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-02-05](https://openairdocs.org/ad/47-02-05): Electrical System · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-02-06](https://openairdocs.org/ad/47-02-06): Hydraulic Hand Pump Shutoff Valve · Boeing C54-DC and DC-4
- [AD 47-12-01](https://openairdocs.org/ad/47-12-01): Openings Around the Control Cables and Flap Buss System · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-12-02](https://openairdocs.org/ad/47-12-02): Center Main Bearings · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-16-01](https://openairdocs.org/ad/47-16-01): Circuit Breaker Switches in Each Nacelle Junction Box · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-16-02](https://openairdocs.org/ad/47-16-02): Flexible Conduit Between the Solenoid and the Firewall Junction Box · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-27-02](https://openairdocs.org/ad/47-27-02): Spar Web Structure · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-27-04](https://openairdocs.org/ad/47-27-04): Exhaust Collector Rings · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-33-01](https://openairdocs.org/ad/47-33-01): Horizontal Stabilizer Outer Hinge Bracket · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-42-01](https://openairdocs.org/ad/47-42-01): Gust Lock Rework · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-42-02](https://openairdocs.org/ad/47-42-02): Cowling Fire Seal · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 47-42-03](https://openairdocs.org/ad/47-42-03): Fire Prevention Changes · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-01-01](https://openairdocs.org/ad/48-01-01): Wheel-Retaining Flange · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-02-02](https://openairdocs.org/ad/48-02-02): Fire Detector Clamp · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-03-02](https://openairdocs.org/ad/48-03-02): Emergency Air Brake · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-06-05](https://openairdocs.org/ad/48-06-05): Control Surface Attachment Rework · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-09-01](https://openairdocs.org/ad/48-09-01): Fuel Transfer Placard · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-09-02](https://openairdocs.org/ad/48-09-02): Electrical Distribution Bus · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-12-01](https://openairdocs.org/ad/48-12-01): Fire Prevention Requirements · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-12-02](https://openairdocs.org/ad/48-12-02): Nose And Cabin Heater Rework · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-14-04](https://openairdocs.org/ad/48-14-04): Tailpipe Shroud Deflector · Boeing C54-DC, C54A-DC, C54B-DC and 2 more
- [AD 48-15-03](https://openairdocs.org/ad/48-15-03): Hydraulic Pressure Regulator Rework · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-17-04](https://openairdocs.org/ad/48-17-04): Vacuum Pumps · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-25-01](https://openairdocs.org/ad/48-25-01): Fire Warning System · Boeing C54-DC and DC-4
- [AD 48-28-02](https://openairdocs.org/ad/48-28-02): Cabin Heater Combustion Ducts · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 48-44-01](https://openairdocs.org/ad/48-44-01): Nose Gear Orifice Fitting · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 49-27-03](https://openairdocs.org/ad/49-27-03): Nose Gear Yoke End And Fittings · Boeing C54-DC and DC-4
- [AD 49-38-02](https://openairdocs.org/ad/49-38-02): Bolt Replacement · Boeing C54-DC, C54A-DC, C54B-DC and 4 more
- [AD 49-46-01](https://openairdocs.org/ad/49-46-01): Vacuum System Fusible Plug · Boeing DC-4, DC-6, DC-6A and 1 more

All 55: https://openairdocs.org/tcds/A-762/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Douglas C54D-DC](https://openairdocs.org/model/douglas-c54d-dc): 2 aircraft (registry code 3021522)
- [Douglas C54E-DC](https://openairdocs.org/model/douglas-c54e-dc): 1 aircraft (registry code 3021528)
- [Douglas C54G-DC](https://openairdocs.org/model/douglas-c54g-dc): 1 aircraft (registry code 3021534)
- [Douglas C54-DC](https://openairdocs.org/model/douglas-c54-dc): 0 aircraft (registry code 3021504)
- [Douglas C54A-DC](https://openairdocs.org/model/douglas-c54a-dc): 0 aircraft (registry code 3021510)
- [Douglas C54B-DC](https://openairdocs.org/model/douglas-c54b-dc): 0 aircraft (registry code 3021516)
- [Douglas DC-4](https://openairdocs.org/model/douglas-dc-4): 0 aircraft (registry code 3021502)
- [Douglas DC4 ATL98-20 CARVAIR](https://openairdocs.org/model/douglas-dc4-atl98-20-carvair): 0 aircraft (registry code 3021501)

## STCs approved under this data sheet (64, first 50)

- [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc.
- [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc.
- [STC SA863EA](https://openairdocs.org/stc/SA863EA): Incorporation of DME Corporation emergency evacuation slide lighting system. Astronics Luminescent Systems Inc
- [STC SA4-492](https://openairdocs.org/stc/SA4-492): Installation of VIP P/N's 104-1-B and 104-1-C engine mount cores.. FTG, Inc.
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA01282NY](https://openairdocs.org/stc/SA01282NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K015 on aircraft powered by Pratt & Whitney radial reciprocating engine Series R-985, R-1340 and R-1830.. Airwolf Filter Corporation
- [STC ST02468AK](https://openairdocs.org/stc/ST02468AK): Installation of a 3 generator electrical system. Alaska Air Fuels Inc
- [STC SA3254WE](https://openairdocs.org/stc/SA3254WE): Nose wheel installation.. United Aeronautical Corporation
- [STC SA3298WE](https://openairdocs.org/stc/SA3298WE): Bendix wheels and brakes installation.. United Aeronautical Corporation
- [STC ST02435AK](https://openairdocs.org/stc/ST02435AK): Installation of four Boeing bulk liquid tanks. Alaska Air Fuel
- [STC ST334CH](https://openairdocs.org/stc/ST334CH): Installation of Superflite 102 fabric.. Aviation Products Systems Inc.
- [STC ST02325AK](https://openairdocs.org/stc/ST02325AK): Installation of four Boeing bulk liquid tanks. Alaska Air Fuel
- [STC SA4-84](https://openairdocs.org/stc/SA4-84): Fiber gasket 4233666 in cowl flap actuating cylinder replaced with AN 6227-20 O ring.. Alaska Airlines Inc
- [STC SA1-115](https://openairdocs.org/stc/SA1-115): Installation of Chamberlain 1012 Series radomes.. Saint-Gobain Performance Plastics Corp
- [STC SA1-507](https://openairdocs.org/stc/SA1-507): 2012X Series radomes.. Saint-Gobain Performance Plastics Corp
- [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc
- [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc.
- [STC SA1365GL](https://openairdocs.org/stc/SA1365GL): Surrendered and incorporated into STC ST334CH.. Cooper Aviation Supply Company, Inc.
- [STC SA300CE](https://openairdocs.org/stc/SA300CE): Installation of Woodward propeller governors on single and twin engine aircraft. (PA-31-325 modified per Colemill STC SA 970SO). Woodward Governor Company
- [STC SA5517NM](https://openairdocs.org/stc/SA5517NM): Limited to installation on serial numbers 27314 and 42994 ONLY.  Installation of a Class "E" cargo compartment, removal of carburetor fluid anti-icing systems, and removal of cabin combustion heater.. Hawaii Pacific Air
- [STC SA3173WE](https://openairdocs.org/stc/SA3173WE): Installation of P&WA R-2000-6 engines in Douglas C54 airplanes.. Globe Air, Inc
- [STC SA1351WE](https://openairdocs.org/stc/SA1351WE): Replace existing fabric on wings, fuselage, empennage, and/or control surfaces, with Ceconite101 material. (262A Series -12). Ceconite Inc
- [STC SA1621CE](https://openairdocs.org/stc/SA1621CE): Restricted category tanker conversion.. Central Air Services
- [STC SA3185WE](https://openairdocs.org/stc/SA3185WE): New enlarged 12 ft cargo door, new cargo floor, structural cargo crash barrier, mod FS 260 bulkhead, relocated main elec junction box, partially new DC elec distribution and control system, DC-6 wheels and brakes, misc changes for cargo operations.. Consulting Aerospace Engineers Inc
- [STC SA3648WE](https://openairdocs.org/stc/SA3648WE): New enlarged 12 ft cargo door, new cargo floor, structural cargo crash barrier, modified FS 260 bulkhead relocated main elec junction box partially new DC elec distribution and control system, DC-6 wheels and brakes, misc changes for cargo operations.. Consulting Aerospace Engineers Inc
- [STC SA1587CE](https://openairdocs.org/stc/SA1587CE): Restricted category tanker conversion. Central Air Services
- [STC SA3603WE](https://openairdocs.org/stc/SA3603WE): Installation of fire retardant tanks.. Waig Aircraft, Inc
- [STC SA1465CE](https://openairdocs.org/stc/SA1465CE): Restricted category tanker conversion. Central Air Services
- [STC SA3790WE](https://openairdocs.org/stc/SA3790WE): Removal of front half of rear cargo door.. Blumenthal James R
- [STC SA1404CE](https://openairdocs.org/stc/SA1404CE): Restricted category tanker conversion. Central Air Services
- [STC SA1334CE](https://openairdocs.org/stc/SA1334CE): Restricted category tanker conversion. Central Air Services
- [STC SA3423WE](https://openairdocs.org/stc/SA3423WE): Installation of 2000 gallon capacity external retardant tank under the fuselage at wing center section. California National Air Services, Inc.
- [STC SA3417WE](https://openairdocs.org/stc/SA3417WE): Increase in height of rear cargo door.. Hamilton Aviation Co
- [STC SA3199WE](https://openairdocs.org/stc/SA3199WE): Cargo handling system installation.. Pemco Engineers, Inc
- [STC SA1744WE](https://openairdocs.org/stc/SA1744WE): Installation of oil filter assemblies.. Nelson Filter
- [STC SA196SO](https://openairdocs.org/stc/SA196SO): Installation of Wright Military Cyclone R-2600-35 engines (as modified per STC SE610SO or R-2600-35 engines having WAD P/N 417916 or 424010 gear boxes).. Charlotte Aircraft Corporation
- [STC SA1117WE](https://openairdocs.org/stc/SA1117WE): Wing flap operated aural warning system.. Potter Aircraft Svc Inc
- [STC SA7SO](https://openairdocs.org/stc/SA7SO): Radome and radar antennae mount provisions for up to 22-inch diameter antennae, RAC AVQ-10 or Bendix RDR-1 (X/C Band).. Tempo Design Corp
- [STC SA108SO](https://openairdocs.org/stc/SA108SO): B-600-1 oil separator.. Air Carrier Eng Service Inc
- [STC SA1183WE](https://openairdocs.org/stc/SA1183WE): RCA AVQ-75 distance measuring equipment (DME).. Johnson Flying Svc Inc
- [STC SA2IN](https://openairdocs.org/stc/SA2IN): Carrying cargo modification.. Aviation Traders Ltd
- [STC SA4-1399](https://openairdocs.org/stc/SA4-1399): Ceconite 101 covering of all fabric-covered surfaces.. Cooper Engineering Corporation
- [STC SA4-163](https://openairdocs.org/stc/SA4-163): Auxiliary fuselage oil tank modification.. California Eastern Aviation Inc
- [STC SA4-203](https://openairdocs.org/stc/SA4-203): Oil filter 1258-B86-C and element1258-OC on aircraft without UD3785 oil temperature regulator.. Winslow Aerofilter Corp
- [STC SA4-204](https://openairdocs.org/stc/SA4-204): Oil filter 1258-B-86-D and element1258-OC on aircraft with UD3785 oil temperature regulator.. Winslow Aerofilter Corp
- [STC SA4-213](https://openairdocs.org/stc/SA4-213): Radio rack in crew compartment.. Asiatic Aeronautical Co., Ltd.
- [STC SA4-317](https://openairdocs.org/stc/SA4-317): Auxiliary oil tank.. Transocean Airlines
- [STC SA4-365](https://openairdocs.org/stc/SA4-365): Emergency inpact light.. Transocean Airlines
- [STC SA4-372](https://openairdocs.org/stc/SA4-372): CO and smoke detection system in belly baggage compartments.. Twentieth Century Aircraft Co
- [STC SA4-414](https://openairdocs.org/stc/SA4-414): Emergency lighting.. California Eastern Aviation Inc

All 64: https://openairdocs.org/tcds/A-762/stcs.md

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