# TCDS 7A1: Maryland Air Industries Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Maryland Air Industries Inc.
- Revision: 20
- Revised: May 13, 1992
- Product: Aircraft, Large Airplane
- Registered aircraft: 1, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/6d/24/6d2497ef10cf417390dd3c025fd58ae64eb8f6581e49f23c2ba3519436be5e9d
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/50EA4CDDB043B005852567270060882C.0001
- Page: https://openairdocs.org/tcds/7A1

## Models (12)

As the data sheet lists them.

- FH-227B
- FH-227C
- FH-227D
- F-27
- F-27A
- F-27M
- F-27J
- FH-227E
- F-27F
- FH-227
- F-27B
- F-27G

## 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
Rev. No. 20 20 20 20 20 20 20 20 20 20 20 20
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
7A1
Revision 20
FAIRCHILD
F-27
F-27A
F-27B
F-27F
F-27G
F-27J
FH-227
FH-227B
FH-227C
FH-227D
FH-227E
F-27M
May 13, 1992
TYPE CERTIFICATE DATA SHEET NO. 7A1
This data sheet which is a part of type certificate No. 7A1 prescribes conditions and limitations under which the product for
which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations.
Type Certificate Holder Maryland Air Industries, Inc.
1424 Davis Ford Road
Woodbridge, Virginia  22192
I - Model F-27 (Transport Category), Approved July 16, 1958; Model F-27A, Approved December 31, 1958;
Model F-27B, Approved October 25, 1958; Model F-27F, Approved February 24, 1961;
Model F-27G, Approved May 1, 1963; Model F-27J, Approved August 3, 1965;
Model FH-227, Approved June 24, 1966; Model FH-227B, Approved February 27, 1967;
Model FH-227C, Approved June 17, 1967; FH-227D and FH-227E, Approved December 21, 1967;
Model F-27M, Approved June 12, 1969.
F-27A same as F-27 except for engine installation.
F-27B same as F-27 except for large forward cargo door.
F-27F same as F-27 except for engine installation.
F-27G same as F-27F except for large forward cargo door.
F-27J same as F-27F except for engine installation.
FH-227 same as F-27J except for 70.8 inch extension to fuselage and major structural changes.
FH-227B same as FH-227 except for propeller installation, wheels and brakes installation and structural changes.
FH-227C same as FH-227 except for propeller installation, wheels and brakes installation.
FH-227D same as FH-227B except for engine installation.
FH-227E same as FH-227C except for engine installation.
F-27M same as F-27J except for propeller and engine installation, elevator trim tab change.
Engines F-27, F-27B : 2 Rolls-Royce Dart 511 or Dart 511-7E or Dart 514-7.
Reduction gearing 0.086:1.
F-27A : 2 Rolls-Royce Dart 528, Dart 528-7E (turboprop).
Reduction gearing 0.093:1.
F-27F, F-27G : 2 Rolls-Royce Dart 529-7E (turboprop).
Reduction gearing 0.093:1.

7A1 2
F-27M : 2 Rolls-Royce Dart 532-7N (turboprop).
Reduction gearing 0.093:1.
F-27J, FH-227 : 2 Rolls-Royce Dart 532-7 (turboprop).
Reduction gearing 0.093:1.
FH-227C, FH-227B: 2 Rolls-Royce Dart 532-7 or 532-7P (turboprop).
Reduction gearing 0.093:1.
FH-227D, FH-227E: 2 Rolls-Royce Dart 532-7L (turboprop).
Reduction gearing 0.093:1.
Fuel (Fuel shall Aviation Kerosene Specifications.
  conform to the
  specifications as United States A.S.T.M. D1655-72 (Jet A or A-1)
  listed or to United States MIL-T-5624H, Grade JP-5
  subsequent revisions Canadian 3-GP-23g
  thereof) 3-GP-24f
British D. Eng. R.D. 2453 Issue 3
2494 Issue 7
2498 Issue 6
U.S.S.R. TS-1 (GOST 10227-62 AM1)
I.A.T.A. Nov. 1969, Kerosene Type Fuel
Aviation Wide-Cut Specifications.
United States A.S.T.M. D1655-72 (Jet B)
United States MIL-T-5624H, Grade JP-4
Canadian 3-GP-22g
British D. Eng. R.D. 2454 Issue 3
2486 Issue 8
I.A.T.A. Nov. 1969, Wide-Cut Fuel
Any mixture of the above type fuels may be used without readjustment of the
engine fuel control unit and without loss in engine power of airplane performance.
Water/Methanol mixture:  to Rolls-Royce Specification AEP-1-W/M
(latest issue).
Oil (Engine and Gearbox) Refer to limitations section of the applicable Airplane Flight Manual for list of approved
engine and gearbox lube oils.

3 7A1
Engine limits Static Sea Level Ratings at ISA
DART 511
Shaft
Horsepower
(shp)
Jet
Thrust
(lb.)
Engine
Speed
(rpm)
Max. Permissible
Turb. Gas Temp.
(°C)
Wet takeoff (5 min.) 1570 310 14,500 595
Dry takeoff 1535 310 14,500 580
Max continuous 1535 310 14,500 580
Starting (momentary) — — — 640
DART 511-7E
Wet takeoff (5 min.) 1570 310 14,500 595
Dry takeoff 1535 310 14,500 625
Max continuous 1535 310 14,500 625
Starting (momentary) — — — 640
DART 514-7
Wet takeoff (5 min.) 1670 332 14,500 600
Dry takeoff 1535 310 14,500 625
Max continuous 1535 310 14,500 625
Starting (momentary) — — — 640
DART 528
Wet takeoff (5 min.) 1870 495 15,000 810
Dry takeoff 1835 485 15,000 780
Max continuous 1835 485 15,000 780
Starting (momentary) — — — 930
DART 528-7E
Wet takeoff (5 min.) 1870 495 15,000 860
Dry takeoff 1835 485 15,000 850
Max continuous 1835 485 15,000 850
Starting (momentary) — — — 930
DART 529-7E
Wet takeoff (5 min.) 1950 510 15,000 860
Dry takeoff 1910 500 15,000 850
Max continuous 1910 500 15,000 850
Starting (momentary) — — — 930
DART 532-7 -7 -7P
Wet takeoff (5 min.) 1990 520 15,000 860 860
Dry takeoff 1835 485 15,000 850 850
Max continuous 1835 485 15,000 850 850
Starting (momentary) — — — 930 930
DART 532-7L
Wet takeoff (5 min.) 2040 520 15,000 905
Dry takeoff 1835 485 15,000 885
Max continuous 1835 485 15,000 885
Starting (momentary) — — — 930
DART 532-7N
Wet takeoff (5 min.) 1990 520 15,000 905
Dry takeoff 1835 485 15,000 885
Max continuous 1835 485 15,000 885
Starting (momentary) — — — 930

7A1 4
Oil Inlet Temperature Dart 511,
511-7E, 514-7
Dart 528, 532-7L, 532-7N,
528-7E, 529-7E, 532-7
Maximum 110° C 120° C
Minimum for starting -30° C -30° C
Minimum for opening power lever -15° C -15°C
Propeller and Dart 511, 511-7E, 514-7 2 Rotol Model (c) R 175/4-30-4/13E, with 4 R.A. 25899 blades each
  propeller limits (F-27, F-27B) Diameter 12.0 ft. (nominal).
  Minimum allowable for repairs 11' 9.75".
  No further reduction permitted.
Pitch settings at .7 radius
  Ground fine pitch 0°
  Flight fine pitch +28° 48'
  Feathered +83°
R.P.M. Limit (Max. 20 sec.) 17,000
Avoid all continuous operation below 7,000 r.p.m.
Dart 528, 528-7E, 2 Rotol Model (c) R 193/4-30-4/50, with 4 R.A. 25907 blades each.
 529-7E, 532-7 Diameter 11.5 ft. (nominal).
(F-27A, F-27F, F-27G,   Minimum allowable for repairs 11' 4.35".
 F-27J, FH-227) Pitch settings at .7 radius
  Ground fine pitch 0°
  Flight fine pitch 20°
  Cruise pitch 32°
  Feathered 87°
R.P.M. Limit (Max. 20 sec.) 16,500
Avoid all continuous operation below 7,000 r.p.m.
Dart 532-7, 532-7L, 2 Rotol Model (c) R 257/4-30-4/60, with 4 R.A. 25941 blades each.
   532-7N, Diameter 12.5 ft. (nominal).
(FH-227B, FH-227C, Minimum allowable for repairs 12' 3.2".
 FH-227D, FH-227E Pitch settings at 0.7 radius
            F-27M)   Ground fine pitch 0°
  Flight fine pitch 16°
  Cruise pitch 28°
  Feathered 83°
R.P.M. Limit (Max. 20 sec.) 16,500 r.p.m.
Avoid all continuous operation between 8,500 and 9,500 r.p.m.
Airspeed limits Vne (Never exceed) 298 m.p.h. (259 kt.)
  (CAS) Vmo (Maximum Operating)
SL - 19,000 ft. 262 m.p.h. (227 kt.)
at 20,000 ft.                                    (226.5 kt.)
above 20,000 ft., Vmo decreases 4.5 kt./1000 ft.
Vmo (Maximum Operating) for FH-227B
    and FH-227D aircraft when modified in accordance
    with Fairchild Service Bulletin FH-227-53-2
    SL-14800 ft. 287 m.p.h. (249 kt.)
    above 14,800 ft. 0.493 MACH.
Va  (Maneuvering and rough-air speed) 177 m.p.h. (154 kt.)
Va  (Maneuvering and rough-air speed)
    for FH-227, FH-227B, FH-227C, FH-227D, and FH-227E 196 m.p.h. (170 kt.)
Vfe (Flaps down to 27°/18°) 161 m.p.h. (140 kt.)
Vfe (Flaps down 27°/18° to full down at 40°/26° 145 m.p.h. (126 kt.)
Vlo (Landing gear operation) 196 m.p.h. (170 kt.)
Vle (Landing gear extended) 196 m.p.h. (170 kt.)

5 7A1
Vmc (Minimum control) for F-27, F-27A
    and F-27B with 0° takeoff flaps
    at sea level standard conditions   96 m.p.h. (  83 kt.)
Vmc (Minimum control) for F-27, F-27A
    and F-27B with 16.5° takeoff flaps
    at sea level standard conditions   90 m.p.h. (  78 kt.)
Vmc (Minimum control) for F-27F, F-27J
    and F-27M with 0° takeoff flaps at
    sea level standard conditions   99 m.p.h. (  86 kt.)
Vmc (Minimum control) for F-27F, F-27J
    and F-27M with 16.5° takeoff flaps
    at sea level standard conditions   93 m.p.h. (  81 kt.)
Vmc (Minimum control) for FH-227,
    FH-227B, FH-227C, FH-227D, and
    FH-227E with 16.5° flaps at sea
    level standard conditions   98 m.p.h. (  85 kt.)
Vmc (Minimum control) for FH-227,
    FH-227B, FH-227C, FH-227D, and
    FH-227E with 0° flaps at sea
    level standard conditions 104 m.p.h. (  90 kt.)
Vmc (Minimum control) for FH-227D
    and FH-227E with 9° flaps at sea
    level standard conditions 101 m.p.h. ( 87.5 kt.)
Maximum speed for extending retractable
type landing light and for operation with light extended 196 m.p.h. (170 kt.)
Vdb (Drag Brake) 262 m.p.h. (227 kt.)
C.G. range For Models F-27, F-27A, F-27B, F-27FF, F-27G, F-27J and F-27M :
Weight Fwd. Aft
(lb.) % M.A.C. Sta. (in.) % M.A.C. Sta. (in.)
(For aircraft with pneumatic nose gear steering system)
Takeoff & landing (gear down) 22,000 21.0 (361.29) 38.0 (378.52)
25,400
to
30,200 20.0 (360.28) 38.0 (378.52)
34,000 24.0 (364.33) 38.0 (378.52)
34,500 24.4 (364.74) 38.0 (378.52)
35,700 25.6 (365.95) 38.0 (378.52)
36,000 25.8 (366.16) 38.0 (378.52)
36,300 26.0 (366.36) 38.0 (378.52)
36,500 26.2 (366.56) 38.0 (378.52)
36,700 26.3 (366.66) 38.0 (378.52)
37,500 27.0 (367.37) 38.0 (378.52)
38,500 27.8 (368.18) 38.0 (378.52)
*39,400 28.4 (368.79) 38.0 (378.52)
*42,000 30.0 (371.41) 38.0 (378.52)
Enroute (gear up) 22,000 Same as Takeoff 40.7 (381.26)
to and Landing
30,200
31,300 20.0 (360.28) 40.7 (381.26)
34,000 23.0 (363.32) 40.7 (381.26)
37,500 25.8 (366.16) 40.7 (381.26)
38,500 26.6 (366.97) 40.7 (381.26)
39,400 27.3 (367.68) 40.7 (381.26)
42,000 29.4 (369.81) 40.7 (381.26)

7A1 6
C.G. range For Models F-27, F-27A, F-27B, F-27FF, F-27G, F-27J and F-27M :   (cont'd)
Weight Fwd. Aft
(lb.) % M.A.C. Sta. (in.) % M.A.C. Sta. (in.)
(For aircraft with hydraulic or pneumatic spur gear steering system.)
Takeoff & landing (gear down) 22,000 21.0 (361.29) 38.0 (378.52)
25,400
to
31,300 20.0 (360.28) 38.0 (378.52)
34,000 23.0 (363.32) 38.0 (378.52)
34,500 23.5 (363.72) 38.0 (378.52)
36,000 24.6 (364.94) 38.0 (378.52)
36,300 24.8 (365.14) 38.0 (378.52)
36,500 25.0 (365.35) 38.0 (378.52)
36,700 25.2 (365.55) 38.0 (378.52)
37,500 25.8 (366.16) 38.0 (378.52)
38,500 26.6 (366.97) 38.0 (378.52)
*39,400 27.3 (367.68) 38.0 (378.52)
40,000 27.8 (368.19) 38.0 (378.52)
*42,000 29.4 (369.81) 38.0 (378.52)
*Takeoff only.
Enroute (gear up) 22,000 21.0 (361.29) 40.7 (381.26)
25,400
to
31,300 20.0 (360.28) 40.7 (381.26)
34,000 23.0 (363.32) 40.7 (381.26)
34,500 23.5 (363.72) 40.7 (381.26)
36,000 24.6 (364.94) 40.7 (381.26)
36,500 25.0 (365.35) 40.7 (381.26)
37,500 25.8 (366.16) 40.7 (381.26)
38,500 26.6 (366.97) 40.7 (381.26)
39,400 27.3 (367.68) 40.7 (381.26)
42,000 29.4 (369.81) 40.7 (381.26)
For Model FH-227:
Takeoff & landing (gear down) 26,000 18.0 (358.25) 35.0 (375.48)
39,000 18.0 (358.25) 35.0 (375.48)
43,500 20.0 (360.28) 35.0 (375.48)
Enroute (gear up) 26,000 18.0 (358.25) 38.0 (378.52)
43,500 18.0 (358.25) 38.0 (378.52)
For Models FH-227B and FH-227D:
Takeoff & landing (gear down) 26,000 25.8 (366.18) 35.0 (375.48)
33,400 18.0 (358.25) 35.0 (375.48)
41,000 18.0 (358.25) 35.0 (375.48)
45,500 20.0 (360.28) 35.0 (375.48)
Enroute (gear up) 26,000 25.8 (366.18) 38.0 (378.52)
33,400 18.0 (358.25) 38.0 (378.52)
41,000 18.0 (358.25) 38.0 (378.52)
45,000 20.0 (360.28) 38.0 (378.52)
For Models FH-227C and FH-227E:
Takeoff & landing (gear down) 26,000 25.8 (366.18) 35.0 (375.48)
33,400 18.0 (358.25) 35.0 (375.48)
41,000 18.0 (358.25) 35.0 (375.48)
43,500 19.1 (359.38) 35.0 (375.48)

7 7A1
For Models FH-227C and FH-227E:     (cont'd)
Weight Fwd. Aft
(lb.) % M.A.C. Sta. (in.) % M.A.C. Sta. (in.)
Enroute (gear up) 26,000 25.8 (366.18) 38.0 (378.52)
33,400 18.0 (358.25) 38.0 (378.52)
41,000 18.0 (358.25) 38.0 (378.52)
43,500 19.1 (359.38) 38.0 (378.52)
F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M:
Linear variation of forward C.G. limit between points shown.
Gear retraction moment change is +27,000 in.-lb.
FH-227:
Linear variation of forward C.G. limit between points shown.
Gear retraction moment change is +29,000 in.-lb.
FH-227B, FH-227C, FH-227D, and FH-227E:
Linear variation of forward C.G. limit between points shown.
Gear retraction moment change is +36,174 in.-lb.
Datum The datum location is variable.  The airplane Weight and Balance report provides the
datum location for that particular airplane.
M.A.C. 101.4 in. (L.E. of M.A.C. +340.0)
Leveling means The leveling means are variable.  The Airplane Weight and Balance report provides
means for that particular airplane.
Maximum weights For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M:
Takeoff 36,225 lb.
36,500 lb. when modified in accordance with Fairchild Service
Bulletin 51-5.
37,500 lb. when modified in accordance with Fairchild
Service Bulletin 51-6.
38,500 lb. when modified in accordance with Fairchild
Service Bulletin 51-7.
39,400 lb. when modified in accordance with Fairchild ECP-233.
40,500 lb. when modified in accordance with Fairchild
ECP-268 or Service Bulletin 51-13.
42,000 lb. when modified in accordance with Fairchild ECP-247.
Landing 34,000 lb.
34,500 lb. when Dowty 9027, Y.4 main landing gear drag
link attachment bolt incorporated.
36,000 lb. when modified in accordance with Fairchild
Service Bulletin 51-5.
36,700 lb. when modified in accordance with Fairchild
Service Bulletin 51-7.
37,500 lb. when modified in accordance with Fairchild ECP-233.
38,500 lb. when modified in accordance with Fairchild
ECP-268 or Service Bulletin 51-13.
40,000 lb. when modified in accordance with Fairchild
ECP-269 or Service Bulletin 51-15 or 51-16.
Zero Fuel, 34,000 lb.
oil and 36,300 lb. when modified in accordance with Fairchild Service
W/M fluid Bulletin 51-7.

7A1 8
Maximum weights (cont'd
For Models FH-227, FH-227B, FH-227C, FH-227D, and FH-227E:
Takeoff 43,500 lb.
45,500 lb. (FH-227B and FH-227D when modified per Fairchild
Service Bulletin FH-227-32-8).
Landing 43,000 lb.
45,000 lb. (FH-227B and FH-227D when modified per Fairchild
Service Bulletin FH-227-32-8).
Zero fuel, 39,000 lb.
oil and 41,000 lb. (FH-227B and FH-227D when modified per
W/M fluid Fairchild Service Bulletin FH-227-32-8).
Minimum crew 2. (Pilot and copilot)
Maximum passengers 48       ).  See Note 1 (d) regarding approved interior arrangements).
Maximum baggage For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M:
Maximum Floor
Capacity Loading
Compartment Station    (lb.)      (#/ft.2)
Fwd. Left 187-230 1200 150
Fwd. Right 154-230 2055 150
Fwd. Left 187-263(1) 2145 150
Fwd. Right 154-263(1) 3000 150
Fwd. Left 187-208   570 150
Fwd. Right 154-208 1444 150
Fwd. Right 136-208 1890 150
Fwd. Right 136-230 2494 150
Fwd. Left 205-230   705 150
Aft 600-681   790(2) 100
(1) Floor reinforcement required in accordance with Fairchild floor assembly Dwg.
No. 27-313131, and installed per Fairchild Dwg. 27-310319.
(2) Maximum capacity for aircraft with heater, air cycle and vapor cycle
systems installed.  REmoval of vapor cycle system increases capacity to 850 lb.;
removal of both the vapor cycle  system and the heater increases limit to 1040 lb.
For Model FH-227, FH-227B, FH-227C, FH-227D, and FH-227E:
Serial Nos. 501-512
Maximum Floor
Capacity Loading
Compartment Station   (lb.)     (#/ft.2)
Fwd. Left (1) 187-230 1200 150
Fwd. Right (1) 154-230 2055 150
Aft 600-691 2200 100
Serial Nos. 513 and up
Fwd. Left (1) 187-230 1200 150
230-265   665 105
Fwd. Left (2) 187-265 1560 105
Fwd. Right (1) 154-230 2055 150
230-265   689 105
Fwd. Right (2) 154-265 2150 105
Aft 600-691 2200 100
(1) Sum of Fwd. Left and Right compartments must not exceed 2200 lb
(2) Sum of Fwd. Left and Right compartments must not exceed 3554 lb

9 7A1
Fuel capacity For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M:
2 outboard tanks of 668 gal. usable fuel each or
2 outboard tanks (ECP 246/256) of 741.5 gal. usable fuel each.
2 inboard tanks (optional) of 182 gal. usable fuel each in accordance with Fairchild
ECP-29, or 2 inboard tanks (optional) of 286 gal. usable fuel each in accordance with
Fairchild ECP-234, or
2 inboard tanks (optional) of 428.5 gal. usable fuel each in accordance with Fairchild
ECP-245/256.
2 collector tanks of 14 gal. usable fuel each.
See NOTE 1(b) for system fuel.
For Models FH-227, FH-227B, FH-227C, FH-227D, and FH-227E:
2 outboard tanks of 668 gal. usable fuel each.
2 collector tanks of 14 gal. usable fuel each.
See NOTE 1(e) for system fuel.
Water-Methanol capacity For Models F-27, F-27A, F-27B, F-27F and F-27G:
80 gal. (total) in two nacelle tanks of 40 gal. each (467.0).
For Models F-27J and F-27M:
120 gal. (total) in two center section tanks of 60 gal. each (378.0)
For Models FH-227, FH-227B, FH-227C, FH-227D, and FH-227E:
Optional for Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and
F-27M 146 gal. (total) in two center section tanks of 73 gal. each (378.0).
Oil capacity 8 gal. (total) in two engine tanks of 4 gal. each (267.5).
See NOTE 1(c) for system oil.
Maximum approved 25,000 ft.
  operating altitude
Other operating The aircraft must be operated in accordance with the FAA Approved Airplane
  limitations Flight Manual.
Control surface movements Elevator Up 25° Down 22°
Elevator Trim Tab (left) Up 12.5° Down 32.5°
"tab trails 3 1/2° down when
cockpit indicator reads zero."
Rudder Right 20° Left 20°
Rudder (FH-227, FH-227B, FH-227C,
FH-227D, and FH-227E) Right 17.5° Left 17.5°
Rudder Balance Tab Right 6° Left 6°
Rudder Trim Tab Right 14° Left 14°
Rudder Trim Tab (FH-227, FH-227B,
FH-227C, FH-227D, and FH-227E) Right 18° Left 18°
Aileron (with spring tab neutral) Up 33° Down 22°
Aileron Spring Tab (inner) Up 13° Down 13°
Aileron Balance Tab (outer) Up 11° Down 16.5°
Aileron Trim Tab (right outer) Up 15° Down 15°
Flaps Down 40°/26°
Serial Nos. eligible For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M:  1 through 500.
For Models FH-227, FH-227C, and FH-227E:  501 and up.
For Models FH-227B and FH-227D:  513 and up.

7A1 10
Certification basis For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M :
CAR 4 b dated December 31, 1953, including Amendment 4b-1, Amendment 4b-3 (Item
21 thru 33 plus Item 39), Amendment 4b-7 and Amendment 4b-8 (Item 17); Special
Regulations SR-422 effective August 27, 1957; and F-27 Special Condition dated
January 28, 1957, as amended.
Type Certificate No. 7A1 issued November 13, 1957; reissued to Fairchild July 16,
1958.
Date of Application for Type Certificate November 9, 1954.
Complies with the following optional requirements:
Ice Protection CAR 4b.640
Ditching CAR 4b.361
(F-27, F-27A, F-27F, F-27J, and F-27M eligible for ditching certification when modified
in accordance with Fairchild Engineering Report No. R27-207 revised April 17, 1959,
when incorporating 44 passenger interior arrangement per Dwg. 27-771164 and related
drawings).
Airplane Flight Manual Supplements Required:
F-27 (with MK-511-7E engines), Supplement I dated September 22, 1959
F-27 (with MK-514-7 engines), Supplement 19 dated February 18, 1963
For Models FH-227, FH-227B, FH-227C, FH-227D, and FH-227E:
CAR 4b dated December 31, 1953, including Amendment 4b-1, Amendment 4b-3,
(Items 21 thru 33 plus Item 39), Amendment 4b-7 and Amendment 4b-8 (Item 17);
Special Regulation SR-422B and SR-450A and F-27 Special Conditions dated
January 28, 1957, as amended.
Complies with the following optional requirements:
Ice Protection CAR 4b.640
Production basis Production Certificate No. 1.
Equipment The basic equipment as prescribed in the applicable airworthiness regulations (see
Certification Basis) must be installed in the aircraft for certification.  In addition, the
following items of equipment are required:
(a) Stall warning system, Fairchild Dwgs. 27-710050/1, 27-721010, 27-740064 (Safe
flight speed control indicator P/N C-30205, included in above Dwgs., is not
required equipment).
(b) FAA Approved Airplane Flight Manual
(1) Model F-27 and F-27B, dated July 18, 1958 reissued April 10, 1959.
Supplement "0" (dated August 5, 1959) required for 36,500 lb. takeoff weight
and 36,000 lb. landing weight.  Supplement "T" (dated April 1, 1960) required
for 37,500 lb. takeoff weight with Dart 511 engine installation.  Supplements
"T" (dated April 1, 1960), "AC" (dated December 9, 1960) and "AF" (dated
November 9, 1961), required for 37,500 lb. takeoff weight with Dart 511-7E
engine installation.  Supplements "AC" (dated December 9, 1960), "AD"
(dated February 20, 1961) and "AF" (dated November 9, 1961), required for
38,500 lb. takeoff, 36,700 lb. landing, and 36,300 lb. zero fuel weights with
Dart 511-7E engine installation.  38,500 lb. takeoff, 36,700 lb. landing, and
36,300 lb. zero fuel weights not applicable to aircraft with Dart 511 engine
installation.

11 7A1
(2) Model F-27 and F-27B with MK-514-7 engines, dated February 18, 1963.
Supplement No. 13 (Rev. 1, dated June 1, 1964) required for 39,400 lb. takeoff
and 37,500 lb. landing gross weights.  Supplement No. 22 (dated June 1, 1964)
required for 40,500 lb. takeoff and 38,500 lb. landing gross weights.
Supplement No. 24 (dated August 3, 1965) required for 40,000 lb. landing
gross weight.
(3) Model F-27A dated December 31, 1958 reissued June 14, 1962. supplement
No. 13 (dated June 14, 1962) required for 39,400 lb. takeoff and 37,500 lb.
landing gross weights. supplement No. 15 (dated November 7, 1962) required
for 42,000 lb. takeoff gross weight.  Supplement No. 17 (dated June 1, 1964)
required for 40,500 lb. takeoff gross weight. Supplement No. 18 (dated June 1,
1964) required for 38,500 lb. landing gross weight.  Supplement No. 21 (dated
August 3, 1965) required for 40,000 lb. landing gross weight.
(4) Model F-27F/F-27G dated February 24, 1961, reissued August 11, 1964.
Supplement No. 13 (dated August 11, 1964) required for 39,400 lb. takeoff,
37,500 lb. landing gross weight.  Supplement No. 17 (dated August 11, 1964)
required for 40,500 lb. takeoff gross weight.  Supplement No. 18 (dated
August 11, 1964) required for 38,500 lb. landing gross weight.  Supplement
No. 19 (dated August 11, 1964) required for 42,000 lb. takeoff gross weight.
Supplement No. 16 (dated August 11, 1964) required for F-27G model only for
convertible passenger - cargo version with large cargo door.  Supplement No.
23 dated August 3, 1965 required for 40,000 lb. landing gross weight.
(5) Model F-27J dated August 3, 1965.
(6) Model FH-227 dated June 24, 1966.
(7) Model FH-227B (Model FH-227 dated June 24, 1966 and Supplement No. 6
dated February 27, 1967) or FH-227B dated June 17, 1967.
(8) Model FH-227C dated June 17, 1967.
(9) Model FH-227D dated December 21, 1967.
(10) Model FH-227E dated December 21, 1967.
(11) Model F-27M dated June 12, 1969.
Service information Service Bulletins 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, when necessary, 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).
(b) System fuel, which must be included in the empty weight, is the amount of fuel required to fill both
systems, including the cross-feed, up to the level of the boost pump inlets in the collector tanks (3.3 gal.
total), plus the unusable fuel of the main tanks (12.1 gal. total).  The total amount of "System Fuel" is as
follows: 15.4 gal. total, 101 lb. (365).
(c) System oil which must be included in empty weight, is the amount of oil normally trapped in the
propellers, plus the amount normally trapped in the engines after oil drainage.  The total amount of
"System Oil" is as follows:
2.4 gal. (total) contained in engines, 19 lb.  (282)
2.0 gal. (total) contained in propellers, 16 lb.  (243)
(d) Fairchild Engineering Reports "Weight and Balance Serial No.      " contain interior arrangement,
equipment list, weight and balance and loading schedule for each airplane.
(e) System fuel, which must be included in the empty weight, is the amount of fuel required to fill both
systems, including the cross-feed, up to the level of the boost pump inlets in the collector tanks (12.0
gal. total), plus the unusable fuel of the main tanks (12.1 gal. total).  The total amount of the "System
Fuel" is as follows:
24.1 gal. total, 161.1 lb. (370.9).

7A1 12
NOTE 2 The following placards must be displayed in the locations indicated:
For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M:
(a) Deleted June 13, 1960.
(b) On the lavatory door (on aircraft with the emergency exit located in the lavatory):
(1) "This door must be open during take-off and landing"
(2) "Emergency exit inside"
(c) On the forward face of the lavatory wall (on aircraft with the emergency exit located in the lavatory):
"Emergency exit thru lavatory"
(d) Deleted June 1, 1963.
(e) On the forward side of the passenger compartment forward door:
"This Door Should be UNLOCKED for Take-off and Landing" (this applies to aircraft
  with life raft stored forward of door).
(f) In the immediate vicinity of swivel seats that do not have the proper back height (36 1/2 in.) in
accordance with TSO C-39 4.1.1.2 and in full view of the passengers:
"This Seat Should Be in The Forward Facing Position During Take-off and Landing".
For Models FH-227, FH-227B, FH-227C, FH-227D, and FH-227E:
(g) Deleted October 1, 1974
(h) On the forward side of the aft passenger bulkhead on either side of the doorway with an appropriate
arrow pointing down at approximately 45°:
"Fire Extinguisher"
(i) Adjacent to the curtain at the aft cargo door:
"This curtain must be held open during take-off and landing"
NOTE 3. Information essential to the proper maintenance of the aircraft is included in the Fairchild F-27 and FH-227
Maintenance Manual provided, with each aircraft.
Current retirement times, which are subject to change, are as follows:
Fuselage to Wing Fitting (27-313619) 40,000 hr.
Fin and Stabilizer Attachment
  Brackets to Fuselage
  27-213002 and 27-213003 40,000 hr.
Cabin Windows (Windows may be replaced on an "as condition basis")
Engine Mount Fittings 25,000 hr. (For Models FH-227, FH-227B,
(P/N's:  27-503148-91, -92)  FH-227C, FH-227D, and FH-227E)
27-503149-51, -52)
The repetitive inspections specified in Fairchild Service Bulletin No. FH-227-51-1
dated July 12, 1967, or later FAA approved revisions, and all FAA approved Supplements
thereto, must be complied with.
......END......
```

## ADs (83, first 50, in force first)

- [AD 2008-22-02](https://openairdocs.org/ad/2008-22-02): Instructions for maintenance and inspection of the fuel tank systems · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Nov 28, 2008
- [AD 2004-22-01](https://openairdocs.org/ad/2004-22-01): Cargo restraint strap assemblies · Cargo restraint straps (Airline Container Manufacturing STC ST01004NY). Effective Dec 1, 2004
- [AD 2002-15-02](https://openairdocs.org/ad/2002-15-02): Compressor Wheels · British Aerospace Regional Jetstream Series 3101, 234, Mystere-Falcon 20 - C5 and 22 more. Effective Aug 28, 2002
- [AD 99-19-09](https://openairdocs.org/ad/99-19-09): AFM - Limitation Section - Ice Protection System · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Dec 27, 1999
- [AD 98-04-31](https://openairdocs.org/ad/98-04-31): AFM - Limitations Section - Icing · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Mar 25, 1998
- [AD 97-23-14](https://openairdocs.org/ad/97-23-14): AFM - Limitations - Power Levers · Maryland Air Industries FH-227, FH-227B, FH-227C and 2 more. Effective Dec 18, 1997
- [AD 97-23-15](https://openairdocs.org/ad/97-23-15): AFM - Limitations - Power Levers · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Dec 18, 1997
- [AD 90-17-13](https://openairdocs.org/ad/90-17-13): Wing Skin Stringers · Maryland Air Industries F-27, F-27A, F-27B and 4 more. Effective Sep 17, 1990
- [AD 90-13-10](https://openairdocs.org/ad/90-13-10): Cockpit Voice & Flight Data Recorders · Maryland Air Industries F-27, F-27A, F-27B and 4 more. Effective Jul 23, 1990
- [AD 90-08-10](https://openairdocs.org/ad/90-08-10): Wing Inspection · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective May 14, 1990
- [AD 87-05-51](https://openairdocs.org/ad/87-05-51): Floor Proximity Lighting · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 48 more. Effective May 18, 1987
- [AD 87-07-05](https://openairdocs.org/ad/87-07-05): Wing-To-Fuselage Fairing · Maryland Air Industries F-27, F-27A, F-27B and 4 more. Effective Apr 20, 1987
- [AD 86-05-09](https://openairdocs.org/ad/86-05-09): Upper Main Undercarriage Drag Stay · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Apr 13, 1986
- [AD 85-21-04](https://openairdocs.org/ad/85-21-04): Rod Assembly · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Nov 14, 1985
- [AD 82-22-51](https://openairdocs.org/ad/82-22-51): Moisture Separator Assembly · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Feb 3, 1983
- [AD 80-18-11](https://openairdocs.org/ad/80-18-11): Horizontal Stabilizer · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Sep 4, 1980
- [AD 73-12-05](https://openairdocs.org/ad/73-12-05): Vertical Stabilizer Fittings · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Aug 29, 1979
- [AD 66-30-04](https://openairdocs.org/ad/66-30-04): Firewall Support Tube Bracket · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Apr 13, 1977
- [AD 76-13-08](https://openairdocs.org/ad/76-13-08): Engine Mount Bolts · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Jul 7, 1976
- [AD 69-05-02](https://openairdocs.org/ad/69-05-02): Wing Panel · Maryland Air Industries FH-227, FH-227B, FH-227C and 2 more. Effective Jun 18, 1976
- [AD 76-10-07](https://openairdocs.org/ad/76-10-07): Large Cargo Door · Maryland Air Industries F-27, F-27A, F-27B and 4 more. Effective Jun 14, 1976
- [AD 76-07-03](https://openairdocs.org/ad/76-07-03): Large Cargo Door · Large cargo door (Fokker50Freighter STC SA2246WE). Effective Apr 6, 1976
- [AD 74-24-09](https://openairdocs.org/ad/74-24-09): Auxiliary Power Units · Airbus BAC 1-11 200 Series, BAC 1-11 400 Series, Auxiliary Power Units and 63 more. Effective Nov 19, 1975
- [AD 73-20-01](https://openairdocs.org/ad/73-20-01): Front and Rear Spar Fittings · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Dec 31, 1974
- [AD 72-07-12](https://openairdocs.org/ad/72-07-12): Stewardess Jump Seat · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Apr 6, 1972
- [AD 76-07-01](https://openairdocs.org/ad/76-07-01): Terminal Board Assembly · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Apr 2, 1972
- [AD 71-08-05](https://openairdocs.org/ad/71-08-05): Main Gear Drag Strut · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Oct 14, 1971
- [AD 70-12-03](https://openairdocs.org/ad/70-12-03): Flap Jackscrew · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Jun 19, 1970
- [AD 68-03-01](https://openairdocs.org/ad/68-03-01): Elevator Trim Tab · Maryland Air Industries FH-227, FH-227B, FH-227C and 2 more. Effective May 27, 1970
- [AD 69-25-04](https://openairdocs.org/ad/69-25-04): Flap Screw Jack End · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Dec 6, 1969
- [AD 69-20-04](https://openairdocs.org/ad/69-20-04): Door Locking Mechanism · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Nov 3, 1969
- [AD 69-21-02](https://openairdocs.org/ad/69-21-02): Cabin Superchargers · British Aerospace Argosy AW.650 Series 101, F27 Mark 100, F27 Mark 300 and 18 more. Effective Oct 9, 1969
- [AD 69-20-07](https://openairdocs.org/ad/69-20-07): Flap Operating System · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Oct 3, 1969
- [AD 69-16-04](https://openairdocs.org/ad/69-16-04): Landing Gear Door Trolley Lever · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Sep 1, 1969
- [AD 69-13-06](https://openairdocs.org/ad/69-13-06): Wing Fuel Access Door Bolts · Maryland Air Industries F-27, F-27A, F-27B and 4 more. Effective Jul 9, 1969
- [AD 69-08-06](https://openairdocs.org/ad/69-08-06): Landing Gear Retraction System · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Apr 23, 1969
- [AD 69-08-01](https://openairdocs.org/ad/69-08-01): Horizontal Stabilizer · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Apr 16, 1969
- [AD 69-06-05](https://openairdocs.org/ad/69-06-05): Inverter · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Apr 15, 1969
- [AD 69-06-01](https://openairdocs.org/ad/69-06-01): Flap Drive System · Maryland Air Industries F-27, F-27A, F-27B and 4 more. Effective Mar 26, 1969
- [AD 69-01-01](https://openairdocs.org/ad/69-01-01): Engine Fire Extinguisher · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Feb 1, 1969
- [AD 69-01-03](https://openairdocs.org/ad/69-01-03): Lower Wing Access Door · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Jan 4, 1969
- [AD 68-23-01](https://openairdocs.org/ad/68-23-01): Cabin Superchargers · British Aerospace Argosy AW.650 Series 101, F27 Mark 100, F27 Mark 300 and 18 more. Effective Nov 21, 1968
- [AD 68-08-03](https://openairdocs.org/ad/68-08-03): Combustion Heater System · Maryland Air Industries F-27, F-27A, F-27B and 4 more. Effective May 19, 1968
- [AD 68-01-05](https://openairdocs.org/ad/68-01-05): Flap Drive System · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Jan 9, 1968
- [AD 67-31-06](https://openairdocs.org/ad/67-31-06): Elevator Trim Tab Hinges · Maryland Air Industries FH-227, FH-227B, FH-227C and 2 more. Effective Dec 1, 1967
- [AD 67-30-03](https://openairdocs.org/ad/67-30-03): Rudder Skin Cracks · Maryland Air Industries F-27A, F-27F, F-27G and 6 more. Effective Nov 1, 1967
- [AD 67-29-02](https://openairdocs.org/ad/67-29-02): Navigation Instruments · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Oct 27, 1967
- [AD 67-29-03](https://openairdocs.org/ad/67-29-03): APU Fire Detection System · Maryland Air Industries F-27J, FH-227, FH-227B and 3 more. Effective Oct 27, 1967
- [AD 67-25-04](https://openairdocs.org/ad/67-25-04): Elongated Rivet Holes · Maryland Air Industries F-27, F-27A, F-27B and 9 more. Effective Sep 8, 1967
- [AD 67-23-04](https://openairdocs.org/ad/67-23-04): Engine Generator Electrical System · Maryland Air Industries F-27J, FH-227, FH-227B and 3 more. Effective Aug 31, 1967

All 83: https://openairdocs.org/tcds/7A1/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Fairchild F-27F](https://openairdocs.org/model/fairchild-f-27f): 1 aircraft (registry code 3373008)
- [Fairchild F-27](https://openairdocs.org/model/fairchild-f-27): 0 aircraft (registry code 3373002)
- [Fairchild F-27A](https://openairdocs.org/model/fairchild-f-27a): 0 aircraft (registry code 3373004)
- [Fairchild F-27B](https://openairdocs.org/model/fairchild-f-27b): 0 aircraft (registry code 3373006)
- [Fairchild F-27G](https://openairdocs.org/model/fairchild-f-27g): 0 aircraft (registry code 3373010)
- [Fairchild F-27J](https://openairdocs.org/model/fairchild-f-27j): 0 aircraft (registry code 3373016)
- [Fairchild F27-M](https://openairdocs.org/model/fairchild-f27-m): 0 aircraft (registry code 3373001)
- [Fairchild F27M](https://openairdocs.org/model/fairchild-f27m): 0 aircraft (registry code 3373018)
- [Fairchild FH-227](https://openairdocs.org/model/fairchild-fh-227): 0 aircraft (registry code 3373042)
- [Fairchild FH-227B](https://openairdocs.org/model/fairchild-fh-227b): 0 aircraft (registry code 3373046)
- [Fairchild FH-227C](https://openairdocs.org/model/fairchild-fh-227c): 0 aircraft (registry code 3373048)
- [Fairchild FH-227D](https://openairdocs.org/model/fairchild-fh-227d): 0 aircraft (registry code 3373050)
- [Fairchild FH-227E](https://openairdocs.org/model/fairchild-fh-227e): 0 aircraft (registry code 3373052)
- [Fokker F27](https://openairdocs.org/model/fokker-f27): 0 aircraft (registry code 4990614)

## STCs approved under this data sheet (143, 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 SA3413NM](https://openairdocs.org/stc/SA3413NM): Installation of Floor Proximity Emergency Escape path Marking System.. Bruce Aerospace Inc.
- [STC ST04359CH](https://openairdocs.org/stc/ST04359CH): Reduction of payload to 7500 lbs. Installation of placard per Rezich & Rezich drawing RR004, Revision NONE, dated August 25, 2017,, or later FAA approved revision.. Rezich and Rezich Aviation Consulting Inc.
- [STC SA43SW](https://openairdocs.org/stc/SA43SW): Structural installation of Collins 137Y-1 doppler antenna and Collins 621C-1 transmitter-receiver.. Associated Air Center, Inc. - c/o CT Corporation System
- [STC SA1134SW](https://openairdocs.org/stc/SA1134SW): Installation of Bendix DRA-12 Doppler Navigation System. Associated Air Center, Inc. - c/o CT Corporation System
- [STC ST00384WI](https://openairdocs.org/stc/ST00384WI): Installation of Keddeg Company P/N 21BC116 Coalescer Assembly. Purolator Facet, Inc
- [STC SA3-682](https://openairdocs.org/stc/SA3-682): Three-Place Divan (for use in F-27).. Sabreliner Aviation LLC
- [STC SA3-683](https://openairdocs.org/stc/SA3-683): Floor Modification and Swivel Chair Installation (Typ) - Hardman Model 3045.. Sabreliner Aviation LLC
- [STC SA3-684](https://openairdocs.org/stc/SA3-684): Double Stationary Chair Installation (Typ) - Burns Model 2DH3EM-2.. Sabreliner Aviation LLC
- [STC SA3-685](https://openairdocs.org/stc/SA3-685): Floor Modification and Track Installation for Swivel Chair (Typ) - Burns Model 2BH1EM-2.. Sabreliner Aviation LLC
- [STC SA3-687](https://openairdocs.org/stc/SA3-687): Relocation of SP-20 Autopilot Amplifier.. Sabreliner Aviation LLC
- [STC SA2016NM](https://openairdocs.org/stc/SA2016NM): Installation of a de-icing system on the Rolls Royce P/N RK29954A engine inlet cowl. ROBERT W. MURRAY
- [STC SA302WE](https://openairdocs.org/stc/SA302WE): Incorporate a de-icing system (as manufactured by applicant) externally on Rotol propeller spinner as an alternate to Dowty Rotol internal elements. If applied to original spinner, Montgomery Systems Tech., Inc. P/N 72196-2 will apply. If applied to a new aluminum nose spinner P/N 72196-1 will apply. Dowty Rotol Service Bulletin Section 61-170 pages 1 and 2 outlines a revised spinner de-icing system. This is a Napier external system. Approval of the A.R.B. is indicated. (Continued on page 3). ROBERT W. MURRAY
- [STC SA253CE](https://openairdocs.org/stc/SA253CE): Installation of Hoskins Supplemental, Model E, High Intensity Wing Tip Lights, Model C Tail Light, with or without Model 2 High Intensity Fuselage Lights.. BF Goodrich Aerospace
- [STC SA3704SW](https://openairdocs.org/stc/SA3704SW): Installation of Floor Proximity Lighting System in accordance with Vista Manufacturing, Inc., Drawing Number F27-1000, Revisions B, Dated December 02, 1986.. BF Goodrich Aerospace
- [STC SA392CE](https://openairdocs.org/stc/SA392CE): Install Hoskins Twilighter Mk V supplementary lighting system including Model E wing tip lights and Model C tal lights.. BF Goodrich Aerospace
- [STC ST177CH](https://openairdocs.org/stc/ST177CH): Installation of AlliedSignal expanded parameter flight data recorders and associated sensors.. Canard Aerospace Corporation
- [STC ST178CH](https://openairdocs.org/stc/ST178CH): Installation of a BFGoodrich Aerospace Jet Electronics and Technology, standby attitude indicator and power supply.. Canard Aerospace Corporation
- [STC SA2246WE](https://openairdocs.org/stc/SA2246WE): Installation of large cargo door. (F27 S/N 21 AND SUBS). Fokker50Freighter STC Corporation
- [STC SA4067NM](https://openairdocs.org/stc/SA4067NM): Installation of Branson Aircraft corporation palletizzed loading system.. Fokker50Freighter STC Corporation
- [STC SA902EA](https://openairdocs.org/stc/SA902EA): Installation of Brownline cargo system.. Fokker50Freighter STC Corporation
- [STC ST01004NY](https://openairdocs.org/stc/ST01004NY): Installation of cargo restraint straps.. Airline Container Manufacturing Co Inc
- [STC SA120SW](https://openairdocs.org/stc/SA120SW): Installation of Collins Autopilot AP-101E with flight director computer 562A-6 or 562A-4A.. Rockwell Collins Inc
- [STC SA190SW](https://openairdocs.org/stc/SA190SW): Installation of Collins Automatic pilot AP-103.. Rockwell Collins Inc
- [STC SA2-842](https://openairdocs.org/stc/SA2-842): Installation of Collins autopilot Model AP-101E.. Rockwell Collins Inc
- [STC SA2773SW](https://openairdocs.org/stc/SA2773SW): Installation of Avionic Systems.. Sierra Industries, Inc
- [STC SA2930SW](https://openairdocs.org/stc/SA2930SW): Replacement of the following avionics systems:  Dual VHF Comm, VHF Nav, Loc, G.S. and transponder, Single Marker, ADF, DME and Weather Radar. Sierra Industries, Inc
- [STC ST415CH](https://openairdocs.org/stc/ST415CH): Install PTC Aerospace seat, number 107862 modified to fit airplane seat rails. (FH-227-B S/N542 ONLY). Proud Bird Interiors
- [STC SA1610SW](https://openairdocs.org/stc/SA1610SW): Installation of Safeway Deicer Boot P/N 5651 and/or Semsa Lead P/N S.2002 in lieu of Dowty Rotol Boot and/or Leads on Dowty Rotol propeller model R193/4-30-4/50 with blades P/N RA 25907.. UNC Accessory Service
- [STC ST00296NY](https://openairdocs.org/stc/ST00296NY): Installation of a Class E cargo interior.. Field Aviation Co, Inc
- [STC SA5161NM](https://openairdocs.org/stc/SA5161NM): Installation of passenger seats and floor modification. Flight Structures Inc
- [STC SA1419GL](https://openairdocs.org/stc/SA1419GL): Installation of Norton lightning diverters.. Norton Company, Performance Plactics
- [STC SA1030SW](https://openairdocs.org/stc/SA1030SW): Interior installation.. Maryland Air Ind Inc
- [STC SA2363WE](https://openairdocs.org/stc/SA2363WE): Installation of interior arrangement.. Maryland Air Ind Inc
- [STC SA670SW](https://openairdocs.org/stc/SA670SW): Electronic system.. Maryland Air Ind Inc
- [STC SA748SW](https://openairdocs.org/stc/SA748SW): Sperry SP-50F autopilot.. Maryland Air Ind Inc
- [STC SA1031SW](https://openairdocs.org/stc/SA1031SW): Installation of electronics system.. Maryland Air Ind Inc
- [STC SA2251WE](https://openairdocs.org/stc/SA2251WE): Installation of Fairchild cockpit voice recorder system and Sundstrand United Data Control flight recorder system.. Maryland Air Ind Inc
- [STC SA4171NM](https://openairdocs.org/stc/SA4171NM): Installation of a Bendix RDR-160/IN152A Weather Radar System. Horizon Air Industries Inc
- [STC SA3706SW](https://openairdocs.org/stc/SA3706SW): Installation of a floor proximity lighting system.. Intl Aircraft Certification Service
- [STC SA1188WE](https://openairdocs.org/stc/SA1188WE): Installation of Collins Radio Company cockpit voice recorder system.. Northwest Airlines, Inc.
- [STC SA1225WE](https://openairdocs.org/stc/SA1225WE): Installation of emergency lighting system.. Northwest Airlines, Inc.
- [STC SA1314WE](https://openairdocs.org/stc/SA1314WE): Installation of either United Control Data Division #V-557 or Fairchild #A-100 cockpit voice recorder system.. Northwest Airlines, Inc.
- [STC SA1333WE](https://openairdocs.org/stc/SA1333WE): Northern Aero Industries, Ltd. cyclic deicing system Model78-10055.. Northwest Airlines, Inc
- [STC SA1406WE](https://openairdocs.org/stc/SA1406WE): Relocation of Fairchild flight data recorder.. Northwest Airlines, Inc.
- [STC SA1496WE](https://openairdocs.org/stc/SA1496WE): Installation of fire detection aural warning system.. Northwest Airlines, Inc.
- [STC SA153WE](https://openairdocs.org/stc/SA153WE): Replacement of nacelle tail cone originally constructed of fibre-glass with a West Coast manufactured tail cone of2024T3 material.. Northwest Airlines, Inc.
- [STC SA1571WE](https://openairdocs.org/stc/SA1571WE): Relocation of Fairchild Model F-542 flight data recorder.. Northwest Airlines, Inc.
- [STC SA3096WE](https://openairdocs.org/stc/SA3096WE): Installation of Collins Radio Co. Model FPC-75 ground proximity warning system.. Northwest Airlines, Inc.
- [STC SA4-1209](https://openairdocs.org/stc/SA4-1209): Cabin air-conditioning modification and addition of inflight cabin air recirculation.. Northwest Airlines, Inc

All 143: https://openairdocs.org/tcds/7A1/stcs.md

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