DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION

2A4
Revision 49
Twin Commander
560-F 685
680 690
680E 690A
680F 690B
680F(P) 690C
680FL 690D
680FL(P) 695
680T 695A
680V 695B
680W 720
681

September 25, 2015

TYPE CERTIFICATE DATA SHEET NO.2A4

This data sheet, which is a part of Type Certificate No. 2A4 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: Twin Commander Aircraft LLC

1176 Telecom Drive
Creedmoor, NC 27522

Type Certificate Holder Record: Aero Design and Engineering Company, also known as Aero Commander Aircraft,
transferred type certificate 2A4 to Rockwell-Standard & Associates in 1958.
Rockwell transferred type certificate 2A4 to Gulfstream American Corporation on
February 3, 1981.
Gulfstream American Corporation transferred type certificate 2A4 to Gulfstream
Aerospace Corporation on November 29, 1981.
Gulfstream Aerospace Corporation transferred type certificate 2A4 to Twin Commander
Aircraft Corporation on December 4, 1989.
Twin Commander Aircraft Corporation transferred type certificate 2A4 to Twin
Commander Aircraft LLC on June 15, 2004.

I - Model 680, 7 PCLM (Normal Category), Approved October 14, 1955 (See NOTE 3 for RL-26-D
(See NOTE 7 for conversion to Model 680E)

Engines 2 Lycoming GSO-480-A1A6, Carburetor Bendix PS-7BD, Part Listing

No. 391663-3, -4, -5, -6, or -7, or GSO-480-B1A6 (See NOTE 4 for –B1A6).

Fuel 100/130 minimum grade aviation gasoline.

Engine Limits (Straight line manifold pressure variation with altitudes shown)
HP. R.P.M. M.P. ALT.
Takeoff 340 3400 48.0 S.L.
Takeoff 340 3400 44.5 8000
Maximum continuous 320 3200 45.0 S.L.
Maximum continuous 320 3200 43.0 8000

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13
Rev. No. 49 49 45 49 49 49 45 49 49 49 49 49 47
Page No. 14 15 16 17 18 19 20 21 22 23 24 25 26
Rev.No. 49 49 47 49 49 49 49 49 49 49 49 49 49
Page No. 27 28 29 30 31 32 33 34
Rev.No. 49 46 49 49 49 45 45 46
2A4 2

I - Model 680 (cont’d)

Propeller and Propeller 2 Hartzell 3-Bladed feathering propellers

Limits a. H.C.-83x20-2 Hubs with 9333c blades
Pitch settings at 30 in. Station: Low 17°, Feather 83°
Diameter: 93 in., no cutoff permitted
NOTE: Letters appearing after the dash numbers of the above listed hub
model do not affect eligibility; however, for best synchronization, hubs
with different numbers should not be combined on the same aircraft.
b. Spinner: 2 Hartzell, Dome C-888-3, Bulkhead C-807-3 or 2 Hartzell
835-10 assemblies or 2 Hartzell 836-7A assemblies (installed with
alcohol anti-icing system per P/N 5890047).
c. Governor: 2 Woodward 210075

Airspeed Limits Maneuvering 160 m.p.h. (139K) True Ind.

Max. Struc. cruising 210 m.p.h. (182K) True Ind.
Never exceed 270 m.p.h. (235K) True Ind.
Flaps extended - half 150 m.p.h. (230K) True Ind.
Flaps extended - full 130 m.p.h. (113K) True Ind.
Landing gear extended 180 m.p.h. (156K) True Ind.

C.G. range (+166.4) to +175.8) (Gear extended)

Effect of retracting landing gear +6655 in.-lb.

Empty Weight C.G. range None

Datum 152 in. forward of wing landing edge at center section.

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams a: front or rear of baggage compartment floor.

Maximum weight 7000 lb.

No. of seats 7 (2 at +95, 2 at +128, and 3 at +168)

Maximum baggage 350 lb. (+200)

Fuel capacity Center tank 158.5 gal. (+187), usable fuel 156 gal. Outboard tanks 33.5 gal. each
(+178), usable fuel 33.5 gal. each.
Total capacity 225.5 gal., usable fuel 223 gal.
(See NOTE 1 for system fuel)

Oil capacity 8.5 gal. total (4.25 gal. each tank) (+191)
8.5 gal. usable (See NOTE 1 for system oil)

Control surface Elevator Up 30°+1 Down 10° +2

-0 -0
Elevator tab Up 2.5° + 2 Down 20° + 2
-½ -0
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flap outboard Down 40° ± 2
Flap inboard Down 40° ± 2

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to
approve design and production charges on airplane serial numbers 680-244-2
to 680-658-255. (See NOTES 15 and 22 for serial number variations and SW-2 status.)
 3 2A4

II. - Model 680-E, 7 PCLM (Normal Category) Approved June 19, 1958
(Same as Model 680 except for extended wing and increased maximum weight)

Engines 2 Lycoming GSO-480-B1A6, Carburetor Bendix PA-7 BD, Part Listing

No. 391663-3, -4, -5, -6, and -7.

Fuel 100/130 minimum grade aviation gasoline.

Engine limits (Straight line manifold pressure variation with altitudes shown)
HP. R.P.M. M.P. ALT.
Takeoff 340 3400 48.0 S.L.
Takeoff 340 3400 44.5 8000
Maximum continuous 320 3200 45.0 S.L.
Maximum continuous 320 3200 43.0 8000

Propeller and Propeller 2 Hartzell 3-Bladed feathering propellers

Limits a. HC-83x20-2 or HC-A3x20-2 Hubs with 9333c blades.
Pitch settings at 30 in. Station: Low 17°, Feather 83°
Diameter: 93 in., no cutoff permitted
NOTE: Letters appearing after the dash numbers of the above listed hub
model do not affect eligibility; however, for best synchronization hubs
with different numbers should not be combined on the same aircraft.
b. Spinner: 2 Hartzell, Dome C-888-3, Bulkhead C-807-3 or 2 Hartzell
835-10 assemblies or 2 Hartzell 836-7A assemblies (installed with
alcohol anti-icing system per P/N 5890047) or 2 Hartzell 836-22S
assemblies (installed with alcohol anti-icing system per P/N 5890047).
c. Governor: 2 Woodward 210075

Airspeed Limits Maneuvering 160 m.p.h. (139K) True Ind.

Max. Struc. cruising 210 m.p.h. (182K) True Ind.
Never exceed 270 m.p.h. (235K) True Ind.
Flaps extended - half 150 m.p.h. (130K) True Ind.
Flaps extended - full 135 m.p.h. (117K) True Ind.
Landing gear extended 180 m.p.h. (156K) True Ind.

C.G. range (+166.0) to (+175.1) (Gear extended)

Effect of retracting landing gear +6655 in.-lb.

Empty Weight C.G. Range None

Datum 152 in. forward of wing leading edge at center section.

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral: Transverse beams at front or rear of baggage compartment floor.

Maximum Weight 7500 lb.

No. of seats 7 (2 at +94, 2 at +128, and 3 at +168)

Maximum baggage 350 lb. (+200)

Fuel capacity Center tank 158.5 gal. (+187), usable fuel 156 gal.
Outboard tanks 33.5 gal. each (+178), usable fuel 33.5 gal. ea.
total capacity 225.5 gal., usable fuel 223 gal.
(See NOTE 1 for system fuel)

Oil capacity 8.5 gal. total (4.25 gal. each tank) (+191)
8.5 gal. usable (See NOTE 1 for system oil)
2A4 4

II. - Model 680-E (cont’d)

Control surface movements Elevator Up 30° + 1 Down 10° + 2
-0 -0
Elevator Tab Up 2 1/2° + 2 Down 20° + 2
-1/2 -0
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flap outboard Down 40° ± 2
Flap inboard Down 40° ± 2

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation Regulations,
Delegation Option Manufacturer No. SW-2 is authorized to approve design and
production changes on airplane serial numbers 680-E-242-102, 680-E-623-1 to
680-E-892-100. (See NOTES 15 and 22 for serial number variations and SW-2 status.)

III. - Model 720, 6 PCLM (Normal Category), Approved December 5, 1958

(Same as Model 680 except for pressurized cabin, structural modifications to the fuselage, extended wing and
increased maximum weight)

Engines 2 Lycoming GSO-480-B1A6, AMC Carburetor Bendix PS-7BD, Part Listing

Nos. 391714-1, -2, -3, and -4.

Fuel 100/130 minimum grade aviation gasoline.

Engine limits (Straight line manifold pressure variation with altitudes shown)
HP R.P.M. M.P. ALT.
Takeoff 340 3400 48.0 S.L.
Takeoff 340 3400 44.5 8000
Maximum continuous 320 3200 45.0 S.L.
Maximum continuous 320 3200 43.0 8000

Propeller and Propeller 2 Hartzell 3-Bladed feathering propellers

Limits a. HC-83x20-2 Hubs with 9333c blades
Pitch settings at 30 in. Station: Low 17°, Feather 83°
Diameter: 93 in., no cutoff permitted
NOTE: Letters appearing after the dash numbers of the above listed hub
model do not affect eligibility; however, for best synchronization hubs
with different numbers should not be combined on the same aircraft.
b. Spinner: 2 Hartzell, Dome C-888-3, Bulkhead C-807-3 or 2 Hartzell
835-10 assemblies or 2 Hartzell 836-7A assemblies (installed with
alcohol anti-icing system per P/N 5890047).
c. Governor: 2 Woodward 210075

Airspeed Limits Maneuvering 160 m.p.h. (139K) True Ind.

Max. Struc. cruising 210 m.p.h. (182K) True Ind.
Never exceed 270 m.p.h. (235K) True Ind.
Flaps extended - half 150 m.p.h. (130K) True Ind.
Flaps extended - full 135 m.p.h. (117K) True Ind.
Landing gear extended 180 m.p.h. (156K) True Ind.

C.G. Range (+166.0) to (+175.1) (Gear extended)

Effect of retracting landing gear +6655 in.-lb.

Empty Weight C.G. Range None

Datum 152 in. forward of wing leading edge at center section.

 5 2A4

III. - Model 720 (cont’d)

Leveling means Longitudinal - top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front or rear of baggage compartment floor.

Maximum weight 7500 lb.

No. of seats 6 (2 at +94, 2 at +128, and 3 at +168)

Maximum baggage 175 lb. (+200)

Fuel capacity Center tank 158.5 gal. (+187), usable fuel 156 gal.
Outboard tanks 33.5 gal. each (+178), usable fuel 33.5 gal. ea.
Total capacity 225.5 gal., usable fuel 223 gal.
(See NOTE 1 for system fuel)

Oil capacity 8.5 gal. total (4.25 gal. each tank) (+191)
8.5 gal. usable (See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 2 1/2° + 2 Down 20° + 2
-1/2 -0
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flap outboard Down 40° ± 2
Flap inboard Down 40° ± 2

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to
approve design and production changes on airplane serial numbers 720-501-1
to 720-850. (See NOTES 15 and 22 for serial number variations and SW-2 status.)

IV - MODEL 680-F, 7 PCLM (Normal Category), Approved August 23, 1960

(Same as 680-E, except for fuel injection engine, new nacelles, new main gear and increased maximum weight.)
(See NOTE 5 for pressurized version).

Engines 2 Lycoming IGSO-540-B1A or IGSO-540-B1C, fuel injector Simmonds Model 580,

Parts Listing No. 580056-B or Model 582 Parts Listing No. 582025 or
Model 582, Parts Listing No. 582026.

Fuel 100/130 minimum grade aviation gasoline.

Engine limits (Straight line manifold pressure variation with altitudes shown)
HP R.P.M M.P. ALT.
Takeoff (2 min.limit) 380 3400 47.0 S.L.
Takeoff (2 min. limit) 380 3400 43.5 12,000
Maximum continuous 360 3200 45.0 S.L.
Maximum continuous 360 3200 40.5 11,500

Propeller and Propeller 2 Hartzell 3-Bladed feathering propellers

Limits a. HC-B3Z-30-2 Hubs with 9349 or 9349-6.5 propellers
Pitch settings at 30 in. Station: Low 18°, Feather 86°
Diameter: (For 9349) 93.5 in.
(For 9349-6.5) 87.0 in., no cutoff permitted
NOTE: Letters appearing after the dash numbers of the above listed hub
model do not affect eligibility; however, for best synchronization hubs
with different numbers should not be combined on the same aircraft.
2A4 6

IV - MODEL 680-F (cont’d) b. Spinner: 2 Hartzell C2504 assemblies or 2 Hartzell C2535 assemblies
(installed with alcohol anti-icing system per P/N 5890047).
c. Governor: 2 Woodward B210310 or 2 Woodward B210410 (when propeller
unfeathering system, Drawing 5640030, is installed). NOTE: Prefix B on
part number or type number denotes based orientation only and may or may
not be stamped on the nameplate. Governor part numbers may differ from
governor type numbers. For best synchronization, governors with
different part numbers should not be combined on the same aircraft.

Airspeed Limits Maneuvering 157 m.p.h. (137K) True Ind.

Max. Struc. cruising 230 m.p.h. (200K) True Ind.
Never exceed 288 m.p.h. (250K) True Ind.
Flaps extended - half 150 m.p.h. (130K) True Ind.
Flaps extended - full 136 m.p.h. (118K) True Ind.
Landing gear extended 180 m.p.h. (156K) True Ind.

C.G. Range (+167.4) to (+174.4) (Gear extended)

Effect of retracting landing gear +10,073 in.-lb.

Empty Weight C.G. Range None

Datum 152 in. forward of wing leading edge at center section.

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front or rear of baggage compartment floor.

Maximum weight 8000 lb.

No. of seats 7 (2 at +94, 2 at +128, and 3 at +168)

Maximum baggage 350 lb. (+200)

Fuel capacity Center tank 158.5 gal. (+187), usable fuel 156 gal.
Outboard tanks 33.5 gal. each (+187), usable fuel 33.5 gal. ea.
Total capacity 225.5 gal., usable fuel 223 gal.
(See NOTE 1 for system fuel)

Oil capacity 10 gal. total (5.00 gal. each tank) (+191)

9.12 gal. usable (See NOTE 1 for system oil)

Control surface Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab* Up 2 1/2° + 2 Down 20° + 2
-1/2 -0
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° ± 2 Left 26° ± 2

Aileron Up 23° ± 2 Down 15° ± 2

Flap outboard Down 40° ± 2
Flap inboard Down 40° ± 2
*Elevator tab Up 2 1/2° + 2 Down 26° + 2
(680-F-971 and up) -1/2 -0

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to
approve design and production changes on airplane serial numbers
680-F-871-1, 680-F-820-2 to 680-F-1447-152. (See NOTES 15 and 22
for serial number variations and SW-2 status.)
 7 2A4

V - Model 560-F, 7 PCLM (Normal Category), Approved February 8, 1961

(Same as Model 680-F except unsupercharged engine and reduced gross weight)

Engine 2 Lycoming IGO-B1A or 2 Lycoming IGO-540 B1C with Aero Commander Vapor
Separator 4630193 installed, fuel injector Bendix Model RS10ED2, Parts
Lifting No. 391825-1 (or any combination of these installations).

Fuel 100/130 minimum grade aviation gasoline.

Engine limits HP. R.P.M.

Takeoff (2 min.) 350 3400
Minimum continuous 325 3000

Propeller and Propeller 1. 2 Hartzell 3-Bladed feathering propellers

Limits a. HC-B3Z-20-2 Hubs with 9349 blades
Pitch settings at 30 in. Station: Low 15°, Feather 87°
Diameter: 93.5 in., no cutoff permitted
NOTE: Letters appearing after the dash numbers of the above
listed hub model do not affect eligibility; however, for best
synchronization hubs with different numbers should not be combined
on the same aircraft.
b. Spinner: 2 Hartzell C2504 assemblies or 2 Hartzell C2535 assemblies
(installed with alcohol anti-icing system per P/N 5890047).
c. Governor: 2 Woodward B210310 or 2 Woodward B210410 (when propeller
unfeathering system, Drawing 5640030, is installed). NOTE: Prefix B
on part number or type number denotes based orientation only and may
or may not be stamped on the nameplate. Governor part numbers may
differ from governor type numbers. For best synchronization, governors
with different part numbers should not be combined on the same aircraft.
2. 2 Hartzell 3-Bladed feathering propellers
a. HC-B3Z-30-2 Hubs with 9349-6.5 blades
Pitch settings at 30 in. Station: Low 18°, Feather 86°
Diameter: 87.0 in., no cutoff permitted
NOTE: Letters appearing after the dash numbers of the above listed hub model
do not affect eligibility; however, for best synchronization hubs with different
numbers should not be combined on the same aircraft.
b. Spinner: 2 Hartzell C2504 assemblies or 2 Hartzell C2535 assemblies
(installed with alcohol anti-icing system per P/N 5890047).
c. Governor: 2 Woodward B210310 or 2 Woodward B210410 (when propeller
unfeathering system, Drawing 5640030, is installed). NOTE: Prefix B
on part number or type number denotes based orientation only and may
or may not be stamped on the nameplate. Governor part numbers may
differ from governor type numbers. For best synchronization, governors
with different part numbers should not be combined on the same aircraft.

Airspeed Limits Maneuvering 155 m.p.h. (135K) True Ind.

Max. Struc. cruising 230 m.p.h. (200K) True Ind.
Never exceed 288 m.p.h. (250K) True Ind.
Flaps extended - half 150 m.p.h. (130K) True Ind.
Flaps extended - full 136 m.p.h. (118K) True Ind.
Landing gear extended 180 m.p.h. (156K) True Ind.

C.G. Range (+167.4) to (+174.4) (Gear extended)

Effect of retracting landing gear +10,073 in.-lb.

Empty Weight C.G. Range None

Datum 152 in. forward of wing leading edge at center section.

2A4 8

V - Model 560-F (cont’d)

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front or rear of baggage compartment floor.

Maximum weight 7500 lb.

No. of seats 7 (2 at +94, 2 at +128, and 3 at +168)

Maximum baggage 350 lb. (+200)

Fuel capacity Center tank 158.5 gal. (+187), usable fuel 156 gal.
Outboard tanks 33.5 gal. each (+178), usable fuel 33.5 gal. ea.
Total capacity 225.5 gal., usable fuel 223 gal.
(See NOTE 1 for system fuel)

Oil capacity 10 gal. total (5.0 gal. each tank) (+191)

9.12 gal. usable (See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 2 1/2° + 2 Down 26° + 2
-1/2 -0
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flap outboard Down 40° ± 2
Flap inboard Down 40° ± 2

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to
approve design and production changes on airplane serial numbers 560-F-951-1
to 560-F-1496-73. (See NOTES 15 and 22 for serial number variations and SW-2 status.)

VI - MODEL 680-FL, 11 PCLM (Normal Category), Approved May 24, 1963

(Same as 680-F, except extended fuselage)

Engines 2 Lycoming IGSO-540-B1A or IGSO-540-B1C, fuel injector Simmonds Model 580,

Parts Listing No. 580056-B or Model 582 Parts Listing No. 582025 or
Model 582 Parts Listing No. 582026. (582026 required for 8500 lb. aircraft.)

Fuel 100/130 minimum grade aviation gasoline

Engine limits (Straight line manifold pressure variation with altitudes shown)

HP R.P.M. M.P. ALT.

Takeoff (2 min. limit) 380 3400 47.0 S.L.
Takeoff (2 min. limit) 380 3400 43.5 12,000
Maximum continuous 360 3200 45.0 S.L.
Maximum continuous 360 3200 40.5 11,500

Propeller and Propeller 2 Hartzell 3-Bladed feathering propellers

Limits a. HC-B3Z-30-2 Hubs with 9349 or 9349-6.5 propellers
Pitch settings at 30 in. Station: Low 28°, Feather 86°
Diameter: (For 9349) 93.5 in.
(For 9349-6.5) 87.0 in., no cutoff permitted
NOTE: Letters appearing after the dash numbers of the above listed hub
model do not affect eligibility; however, for best synchronization hubs
with different numbers should not be combined on the same aircraft.
 9 2A4

VI - Model 680-FL (cont’d) b. Spinner: 2 Hartzell C2504 assemblies

c. Governor: 2 Woodward B210310 or 2 Woodward B210410 (when propeller
unfeathering system, Drawing 5640030, is installed). NOTE: Prefix B on
part number or type number denotes based orientation only and may or may
not be stamped on the nameplate. Governor part numbers may differ from
governor type numbers. For best synchronization, governors with
different part numbers should not be combined on the same aircraft.

Airspeed Limits Maneuvering 157 m.p.h. (137K) True Ind. @ 8000 lb.
161 m.p.h. (140K) True Ind. @ 8500 lb.
Max. Struc. cruising 230 m.p.h. (200K) True Ind. @ 8000 lb. and 8500 lb.
Never exceed 288 m.p.h. (250K) True Ind. @ 8000 lb. and 8500 lb.
Flaps extended - half 150 m.p.h. (130K) True Ind. @ 8000 lb. and 8500 lb.
Flaps extended - full 136 m.p.h. (118K) True Ind. @ 8000 lb.
146 m.p.h. (127K) True Ind. @ 8500 lb.
Landing gear extended 180 m.p.h. (156K) True Ind. @ 8000 lb. and 8500 lb.

C.G.Range Weight Fwd. Aft.

(Gear extended) lb. Sta.(in)% MAC Sta.(in) % MAC
Up to 7000 203.0 l0 218.4 32
8000 206.5 15 218.4 32
8500 208.3 17.5 218.4 32
Straight line variation between points given
Effect of retracting landing gear +10,073 in.-lb.

Empty Weight C.G. Range None

Datum 196 in. forward of wing leading edge at center section.

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front or rear of baggage compartment floor.

Maximum weight (See NOTE 6 for approved weights)

No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers)

Maximum baggage (std) 400 lb. (+258)

Maximum baggage (with 600 lbs. (+258)

extended baggage compartment)

Fuel capacity Center tank 158.5 gal. (+231), usable fuel 156 gal.
Outboard tanks 33.5 gal. each (+222), usable fuel 33.5 gal. ea.
Total capacity 225.5 gal., usable fuel 223 gal. (See NOTE 1 for system fuel)

Oil capacity 10 gal. total (5.00 gal. each tank) (+235)

9.12 gal. usable (See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 2 1/2° + 2 Down 26° + 2
-1/2 -0
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flap outboard Down 40° ± 2
Flap inboard Down 40° ± 2
2A4 10

VI - Model 680-FL (cont’d)

Serial Nos. eligible (See NOTE 6 for serial numbers). Under the delegation option, provisions of Part 21
of the Federal Aviation Regulations, Delegation Option Manufacturer No. SW-2 is
authorized to: Issue Airworthiness Certificates for airplane serial numbers
680-FL-1553-107 and up; and approve design and production changes on airplane serial
numbers 680-FL-1261 through 1853-157. (See NOTES 15 and 22 for serial number
variations and SW-2 status.)

VII - MODEL 680-FL(P), 11 PCLM (Normal Category), approved October 8, 1964

(Same as 680-FL, S/N 1461 and up, except pressurization)

Engines 2 Lycoming IGSO-540-B1A or IGSO-540-B1C, fuel injector Simmonds Model 582,

Parts Listing No. 582026.

Fuel 100/130 minimum grade aviation gasoline.

Engine limits (Straight line manifold pressure variation with altitudes shown)
HP. R.P.M M.P. ALT.
Takeoff (2 min. limit) 380 3400 47.0 S.L.
Takeoff (2 min. limit) 380 3400 43.5 12,000
Maximum continuous 360 3200 45.0 S.L.
Maximum continuous 360 3200 40.5 11,500

Propeller and Propeller 2 Hartzell 3-Bladed feathering propellers

limits a. HC-B3Z-30-2 Hubs with 9349-6.5 blades
Pitch settings at 30 in. Station: Low 18°, Feather 86°
Diameter: 87.0 in., no cutoff permitted
NOTE: Letters appearing after the dash numbers of the above listed hub
model do not affect eligibility; however, for best synchronization hubs
with different numbers should not be combined on the same aircraft.
b. Spinner: 2 Hartzell C2504 assemblies
c. Governor: 2 Woodward B210310 or 2 Woodward B210410 (when propeller
unfeathering system, Drawing 5640030, is installed). NOTE: Prefix B on
part number or type number denotes based orientation only and may or may
not be stamped on the nameplate. Governor part numbers may differ from
governor type numbers. For best synchronization, governors with
different part numbers should not be combined on the same aircraft.

Airspeed Limits Maneuvering 161 m.p.h. (140K) True Ind.

Max. Struc. cruising 230 m.p.h. (200K) True Ind.
Never exceed 288 m.p.h. (250K) True Ind.
Flaps extended - half 150 m.p.h. (130K) True Ind.
Flaps extended - full 146 m.p.h. (127K) True Ind.
Landing gear extended 180 m.p.h. (156K) True Ind.

C.G. Range Weight Fwd. Aft.

(Gear extended) lb. Sta.(in)% MAC Sta.(in) % MAC
Up to 7000 203.0 l0 218.4 32
8500 208.3 17.5 218.4 32
Straight line variation between points given.
Effect of retracting landing gear +10,073 in.-lb.

Empty Weight C.G. Range None

Datum 196 in. forward of wing leading edge at center section

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front or rear of baggage compartment floor.

Maximum weight 8500 lb.

 11 2A4

VII - MODEL 680-FL(P) (cont’d)

Maximum No. of seats 11 (Pilot - 10 passengers; pilot, co-pilot +9 passengers)

Maximum baggage 400 lb. (+258)

Fuel capacity Center tank 158.5 gal. (+231), usable fuel 156 gal.
Outboard tanks 33.5 gal. each (+222), usable fuel 33.5 gal. ea.
Total capacity 225.5 gal. usable fuel 223 gal. (See NOTE 1 for system fuel)

Oil capacity 10 gal. total (5.00 gal. each tank) (+235)

9.12 gal. usable (See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 2 1/2° + 2 Down 26° + 2
-1/2 -0
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flap outboard Down 40° ± 2
Flap inboard Down 40° ± 2

Serial No. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates for airplane serial numbers 680-FLP-1559-25
and up; and approve design and production changes on airplane serial numbers
680-FLP-1471-2 through 1854-38. (See NOTES 15 and 22 for serial number
variations and SW-2 status.)

VIII - MODEL 680-T - 11 PCLM (Normal Category), approved September 15, 1965
(See NOTE 9 conversion to Model 680V)

Engines 2 AiResearch Model TPE-331-43 Turboprop engines (Rockwell P/N 6610400-501)

or TPE-331-43A (Rockwell P/N 6610400-505) (See NOTE 11 for requirements)

Fuel Aviation turbine fuels ASTM designation D1655-63T, Types Jet A, Jet B, and
Jet A-1; and MIL-J-5624G(1), Grades JP-4 & JP-5 and MIL-F-5516-1, JP-1
(See Aerocom Serv. Ltr. 170)

Oil BRACO 880F (MIL-L-7808D) and Sinclair Turbo S Oil 15 (MIL-L-7808D&E)

(See Aerocom Service Letter 170)

Engine limits HP. R.P.M. EGT

Takeoff 575 100% 576°C
Maximum continuous 500 100% 550°C

Propeller and Propeller 2 Hamilton Standard 3-bladed feathering and reversing propellers
Limits Rockwell Assembly No. 640050.
a. 33LF-325 Hubs with 1033A-O Blades
Pitch settings at 30 in. Station: Flt. Idle 9.0° ± 0.2°,
Feather 86.5° ± 0.5°, Reverse -9.5° ± 1.5°
Diameter: 90 in., no cutoff permitted.
NOTE: Use AiResearch oil transfer tube No. 866678-2.
b. Spinner: 2 Rockwell 2640050-7
c. Governor: 2 AiResearch 865423-4 or 865423-5-1
2A4 12

VIII - MODEL 680-T (cont’d)

Airspeed Limits Maneuvering 164 m.p.h. ((143K) CAS
Maximum Operating 250 m.p.h. (217K) CAS
Flaps extended - half 150 m.p.h. (130K) CAS
Flaps extended - full 146 m.p.h. (127K) CAS
Landing gear extended 180 m.p.h. (156K) CAS

C.G. range Rear: 217.78 (30.19%) 8950 lbs. (Gear down

216.94 (29.02%) 5300 lbs. (Gear down)
Fwd: 208.14 (16.83%) 8950 lbs. (Gear down)
203.50 (10.40%) 7500 lbs. (Gear down)
Straight line variation between points given.
Effect of retracting landing gear +10,073 in.-lb.

Datum 196 in. forward of wing landing edge at center section

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of rear baggage compartment floor.

Maximum weight Maximum takeoff 8950 lbs. (ramp weight 9000 lbs.)
Maximum landing 8500 lbs.

Maximum operating altitude 25,000 feet

Maximum No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers)

Maximum baggage 400 lb. (+258)

Fuel capacity Center tank 221.5 gal. (+231), usable fuel 219.5 gal.
Outboard tanks 33.5 gal. each (+222), usable fuel 33.5 gal. ea.
Total capacity 288.5 gal., usable fuel 286.5 gal.
(See NOTE 1 for system fuel) (See NOTE 12 for auxiliary fuel)

Oil capacity 15.0 qts. total (7.5 qts. each tank) (+188)
11.8 qts. usable (See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 6 1/2° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flap outboard Down 40° ± 2
Flap inboard Down 40° ± 2

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates for airplane serial numbers 680-T-1473,
680-T-1519, 680-T-1532, 680-T-1536, and 680-T-1550-11 and up; and approve
design and production changes on airplane serial numbers 680-T-1473 through
1720. (See NOTES 15 and 22 for serial number variations and SW-2 status.)
 13 2A4

IX - MODEL 680-V, 11 PCLM (Normal Category), Approved June 13, 1967

Engines 2 AiResearch Model TPE-331-43 Turboprop engines (Rockwell P/N 6610400-501)
or TPE-331-43A (Rockwell P/N 6610400-505) (See NOTE 11 for requirements).

Fuel Aviation turbine fuels ASTM designation D1655-63T, Types Jet A, Jet B, and
Jet A-1; and MIL-J-5624G(1), Grades JP-4 & JP-5 and MIL-F-5616-1, JP-1.
(See Aerocom Serv. Ltr. 170)

Oil BRACO 880F (MIL-L-7808D) and Sinclair Turbo S Oil 15 (MIL-L-7808D&E)

(See Aerocom Service Letter 170)

Engine Limits HP. R.P.M. EGT

Takeoff 575 100% 576°C
Maximum continuous 500 100% 550°C

Propeller and Propeller 2 Hamilton Standard 3-bladed feathering and reversing propellers.
Limits Rockwell Assembly No. 640050.
a. 33LF-325 Hubs with 1033A-0 blades
Pitch settings at 30 in. Station: Flt. Idle 9.0° ± 0.2°
Feather 86.5° ± 0.5°, Reverse -9.5° ± 1.5°
Diameter: 90 in., no cutoff permitted
NOTE: Use AiResearch oil transfer tube No. 866678-2.
b. Spinner: 2 Rockwell 2640050-7
c. Governor: 2 AiResearch 865423-4 or 865423-5-1

Airspeed Limits Maneuvering 164 m.p.h. (143K) CAS

Maximum Operating 250 m.p.h. (217K) CAS
Flaps extended - half 150 m.p.h. (130K) CAS
Flaps extended - full 146 m.p.h. (127K) CAS
Landing gear extended 180 m.p.h. (156K) CAS

C.G. Range Rear: 215.68 (27.28%) 9450 lbs. (Gear down)

216.73 (28.73%) 9400 lbs. (Gear down)
217.87 (30.31%) 9346 lbs. (Gear down)
216.94 (29.02%) 5300 lbs. (Gear down)
Fwd: 209.74 (19.04%) 9450 lbs. (Gear down)
209.60 (18.83%) 9400 lbs. (Gear down)
203.50 (10.40%) 7500 lbs. (Gear down)
Straight line variation between points given.
Effect of retracting landing gear +10,073 in.-lb.

Datum 196 in. forward of wing leading edge at center section.

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of rear baggage compartment floor.

Maximum weight Maximum takeoff 9400 lbs. (ramp weight 9450 lbs.)
Maximum landing 9000 lbs.
Zero fuel 8000 lbs.

Maximum operating altitude 25,000 feet

Maximum No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers)

Maximum baggage 500 lb. (+258)

Fuel capacity Center tank 221.5 gal. (+231), usable fuel 219.5 gal.
Outboard tanks 33.5 gal. each (+222), usable fuel 33.5 gal. ea.
Total capacity 288.5 gal., usable fuel 286.5 gal.
(See NOTE 1 for system fuel) (See NOTE 12 for auxiliary fuel).
2A4 14

IX - MODEL 680-V, 11 PCLM (Normal Category), Approved June 13, 1967

Oil capacity 15.0 qts. total (7.5 qts. each tank) (+188)
11.8 qts. usable (See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 6 1/2° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flap outboard Down 40° ± 2
Flap inboard Down 40° ± 2

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates for airplane serial numbers 680-V-1550
through 680-V-1725; and approve design and production changes on airplane
serial numbers 680-V-1473 through 1720. (See NOTES 15 and 22 for serial
number variations and SW-2 status.)

X - MODEL 680-W, 11 PCLM (Normal Category), approved February 5, 1968

Engines 2 AiResearch Model TPE-331-43BL Turboprop engines (Rockwell P/N 6610400-503)

Fuel Aviation turbine fuels ASTM designation D1655-63T, Types A, Jet B, and
Jet A-1; and MIL-J-5624G(1), Grades JP-4 & JP-5; and MIL-F-5616-1, JP-1,
(See Aerocom Serv. Ltr. 170)

Oil BRACO 880F (MIL-L-7808D) and Sinclair Turbo S Oil 15 (MIL-L-7808D&E)

(See Aerocom Service Letter 170)

Engine limits HP. R.P.M. EGT

Takeoff 575 100% 576°C
Maximum continuous 500 100% 550°C

Propeller and Propeller 2 Hamilton Standard 3-bladed feathering and reversing propellers.
Limits Rockwell Assembly No. 640050.
a. 33LF-325 Hubs with 1033A-0 Blades
Pitch settings at 30 in. Station: Flt. Idle 9.0° ± 0.2°,
Feather 86.5° ± 0.5°, Reverse -9.5° ± 1.5°.
Diameter: 90 in., no cutoff permitted.
NOTE: Use AiResearch oil transfer tube No. 866678-2.
b. Spinner: 2 Rockwell 2640050-7
c. Governor: 2 AiResearch 869132-2-1

Airspeed Limits Maneuvering 164 m.p.h. (143K) CAS

Maximum Operating 250 m.p.h. (217K) CAS
Flaps extended - half 150 m.p.h. (130K) CAS
Flaps extended - full 146 m.p.h. (127K) CAS
landing gear extended 180 m.p.h. (156K) CAS

C.G. Range Rear: 215.68 (27.28%) 9450 lbs. (Gear down)

216.73 (28.73%) 9400 lbs. (Gear down)
217.87 (30.31%) 9346 lbs. (Gear down)
216.94 (29.02%) 5300 lbs. (Gear down)
Fwd.: 209.74 (19.04%) 9450 lbs. (Gear down)
209.60 (18.83%) 9400 lbs. (Gear down)
203.50 (10.40%) 7500 lbs. (Gear down)
Straight line variation between points given.
Effect of retracting landing gear +10,073 in.-lb.
 15 2A4

X - MODEL 680-W (cont’d)

Datum 196 in. forward of wing leading edge at center section.

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of each baggage compartment floor.

Maximum weight Maximum takeoff 9400 lbs. (ramp weight 9450 lbs.)
Maximum landing 9000 lbs.
Zero fuel 8000 lbs.

Maximum operating altitude 25,000 feet

Maximum No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers)

Maximum baggage 500 lb. (+258) Serial numbers eligible for Model 680-W-1721 through 1850.

Fuel capacity Center tank 221.5 gal. (+231), usable fuel 219.5 gal.
Outboard tanks 33.5 gal. each (+222), usable fuel 33.5 gal. ea.
Total capacity 288.5 gal., usable fuel 286.5 gal.
(See NOTE 1 for system fuel.) (See NOTE 12 for auxiliary fuel.)

Oil capacity 15.0 qts. total (7.5 qts. each tank) (+188)
11.8 qts. usable (See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 6 1/2° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flap outboard Down 40° ± 2
Flap inboard Down 40° ± 2

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates and approve design and production changes
on airplane serial numbers 680-W-1721 through 1850, (See NOTES 15 and 22
for serial number variations and SW-2 status.)

XI - MODEL 681, 11 PCLM (Normal Category), Approved March 20, 1969

Engines 2 AiResearch Model TPE-331-43BL Turboprop engines (Rockwell P/N 6610400-507)

Fuel Aviation turbine fuels ASTM designation D1655-64T, Types Jet A, Jet B, and Jet A-1;
and MIL J-5624G(1), Grades JP-4 & JP-5. (See Aerocom Service Letter 170)

Oil BRACO 880F (MIL-L-7808D) and Sinclair Turbo S Oil 15 (MIL-L-7808D&E)

(See Aerocom Service Letter 170)

Engine limits HP. R.P.M. EGT

Takeoff 575 100% 576°C
Maximum continuous 500 100% 550°C
2A4 16

XI - MODEL 681 (cont’d)

Propeller and Propeller 2 Hamilton Standard 3-bladed feathering and reversing propellers
limits Rockwell Assembly No. 640050.
a. 33LF-325 Hubs with 1033 A-0 Blades
Pitch settings at 30 in. Station: Flt. Idle 9.0° ± 0.2°
Feather 86.5° ± 0.5°, Reverse -9.5 ° ± 1.5°
Diameter: 90 in., no cutoff permitted.
NOTE: Use AiResearch oil transfer tube No. 866678-2.
b. Spinner: 2 Rockwell 2640050-7
c. Governor: 2 AiResearch 869132-2-1

Airspeed Limits Maneuvering 164 m.p.h. (143K) CAS

Maximum Operating 250 m.p.h. (217K) CAS
Flaps extended - half 150 m.p.h. (130K) CAS
Flaps extended - full 149 m.p.h. (129K) CAS
Landing gear extended 180 m.p.h. (156K) CAS

C.G. Range Rear: 215.68 (27.28%) 9450 lbs. (Gear down)

216.73 (28.73%) 9400 lbs. (Gear down)
217.87 (30.31%) 9346 lbs. (Gear down)
216.94 (29.02%) 5300 lbs. (Gear down)
Fwd.: 209.74 (19.04%) 9450 lbs. (Gear down)
209.60 (18.83%) 9400 lbs. (Gear down)
203.50 (10.40%) 7500 lbs. (Gear down)
Straight line variation between points given.
Effect of retracting landing gear +10,073 in.-lb.

Datum 196 in. forward of wing leading edge at center section

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of rear baggage compartment floor.

Maximum weight Maximum takeoff 9400 lbs. (ramp weight 9450 lbs.)
Maximum landing 9000 lbs.
Zero fuel 8500 lbs.

Maximum operating altitude 25,000 feet

Maximum No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers)

Maximum baggage 500 lb. (+258)

Fuel capacity Center tank 221.5 gal. (+231), usable fuel 219.5 gal.
Outboard tanks 33.5 gal. each (+222), usable fuel 33.5 gal. ea.
Total capacity 288.5 gal., usable fuel 286.5 gal.
(See NOTE 1 for system fuel) (See NOTE 12 for auxiliary fuel)

Oil capacity 15.0 qts. total (7.5 qts. each tank) (+188)
11.8 qts. usable (See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 6 1/2° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flap outboard Down 40° ± 2
Flap inboard Down 40° ± 2
 17 2A4

XI - MODEL 681 (cont’d)

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates and approve design and production changes
on airplane serial numbers 681-6001 through 6072. (See NOTES 15 and 22
for serial number variations and SW-2 status.)

XII - MODEL 690, 11 PCLM (Normal Category), approved July 19, 1971

Engines 2 AiResearch Model TPE-331-5-251K Turboprop engines (Rockwell P/N 610495)

Fuel Aviation turbine fuels ASTM designation D1655-68, Types Jet A, Jet B, and
Jet A-1; and MIL-T-5624G(1), Grades JP-4 & JP-5. (See Rockwell Service
Letter 170H)

Oil MIL-L-23699A and MIL-L-7808G. (See Rockwell Service Letter 170H)

Engine limits HP. R.P.M. I.T.T.

Takeoff 717.5 101% 923°C
Maximum continuous 717.5 101% 923°C

Propeller and Propeller 2 Hartzell 3-bladed feathering and reversing propellers.

limits Rockwell Assembly No. 640053.
a. HC-B3TN-5FL Hubs with LT10282H-4 or LT10282H(B)+4 or LT10282+4 or
LT10282(B)+4 or LT10282A+4 or LT10282AB+4 blades
OR HC-B3TN-5DL or HC-B3TN-5NL hubs with LT10282A+4 or
LT10282AB+4 blades.
Pitch settings at 30 in. Station: Low 13.5° ± 0.2°,
Feather 90.0° ± 0.5°, Reverse -8.0° ± 0.5°,
Start Locks +2.5° ± 0.2°
Diameter: 106 in, 1/2 in. reduction per blade allowed.
NOTE: Use AiResearch oil transfer tube No. 866533-3.
See NOTE 16 for alternate blades.
b. Spinner: 2 Hartzell 836-57
c. Governor: 2 AiResearch 895490-1 or 895490-3.

Airspeed Limits Maneuvering 167 m.p.h. (145K) CAS

Maximum Operating 280 m.p.h. (234K) CAS
Flaps extended - half 180 m.p.h. (156K) CAS
Flaps extended - full 157 m.p.h. (136K) CAS
Landing gear extended 230 m.p.h. (200K) CAS

C.G. Range Forward

212.93 inches aft of datum (22.72% MAC) at 10,250 lbs.
203.75 inches aft of datum (10.40% MAC) at 7,500 lbs.
203.75 inches aft of datum (10.40% MAC) at 5,750 lbs.
Straight line variation between points.

Aft
218.70 inches aft of datum (30.47% MAC) at 10,250 lbs.
217.81 inches aft of datum (29.28% MAC) at 5,750 lbs.
Variation between points:
Inches aft of datum = 219.84 - (11653/Weight)

Datum 196 in. forward of wing leading edge at center section.

Leveling means Longitudinal - top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beam at front of rear baggage compartment floor.
2A4 18

XII - MODEL 690 (cont’d)

Maximum weight Maximum takeoff 10,250 lbs. (ramp weight 10,300 lbs.)
Maximum loading 9600 lbs.
Zero fuel 8750 lbs.

Maximum operating altitude 25,000 feet

Maximum No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers)

Maximum baggage 600 lbs. (+260)

Fuel capacity Total capacity 389.0 gal., usable fuel 384.0 gal.
(see NOTE 1 for system fuel)

Oil capacity Oil capacity per engine @ +188

AiResearch Tank No. 896062-1 6.25 qt. total 5.25 qt. usable
AiResearch Tank No. 896417-1 6.00 qt. total 5.00 qt. usable
(See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 0
Elevator tab Up 6 1/2° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flaps Down 40° ± 2
Aileron tab Up 17° ± 2.5° Down17° ± 2.5°

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificate and approve design and production changes
on airplane serial numbers 690-11001 through 11099. (See NOTES 15 and 22
for serial number variations and SW-2 status.)

XIII - MODEL 685, 9 PCLM (Normal Category), Approved September 17, 1971

Engines 2 Continental Model GTSIO-520-F or GTSIO-520-K Turbosupercharged engines

(See NOTE 14 for –K requirements) (Rockwell P/N 610503)

Fuel Aviation gasoline, 100/130 octane.

Oil Teledyne Continental Specification MHS-24A.

Engine limits HP R.P.M. M.A.P.

Takeoff 435 3400 44.5 In.Hg
Maximum continuous 435 3400 44.5 In.Hg

Propeller and Propeller 2 Hartzell 3-bladed feathering propellers

limits Rockwell Drawing No. 610505
a. HC-H3YN-2 or HC-H3YN-2F Hubs with C8475+2, FC8475+2, or FC8475B+2
blades.
Pitch settings at 30 in. Station: Low 18.1° ± 1.0°
Feathered 83.5° ± 1.0°
Diameter: 88 in., 1/2 in. reduction per blade allowed.
b. Spinner: 2 Hartzell D-3273-1
c. Governor: 2 Rockwell 610445-1, 610445-501, or 610445-503
 19 2A4

XIII - MODEL 685 (cont’d)

Airspeed Limits Maneuvering 156 m.p.h. (136K) CAS
Never exceed 290 m.p.h. (252K) CAS
Never exceed Mach 0.554
Flaps extended - half 180 m.p.h. (156K) CAS
Flaps extended - full 149 m.p.h. (130K) CAS
Landing gear extended 230 m.p.h. (200K) CAS
Max structural cruise 258 m.p.h. (224K)

Max. structural cruise Mach 0.493

C.G.Range Rear: 216.88 (28.0%) 9,000 lbs. (Gear down)
216.18 (27.1%) 5, 850 lbs. (Gear down)
Variation between points: inches = 218.15 - (11653/Weight)
Fwd: 208.67 (17.0%) 9,000 lbs. (Gear down)
203.45 (10.0%) 7,500 lbs. (Gear down)
203.45 (10.0%) 5,850 lbs. (Gear down)
Straight line variation between points given. Effect of retracting landing
gear +11,653 in.-lb.

Datum 196 in. forward of wing leading edge at center section.

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of rear baggage compartment floor.

Maximum weight Maximum takeoff 9000 lbs. (ramp weight 9050 lbs.)
Maximum landing 9000 lbs.

Maximum operating altitude 25,000 feet

Maximum number of seats 9 (Pilot + 8 passengers; pilot, co-pilot + 7 passengers)

Maximum baggage 600 lb. (+260)

Fuel capacity Total capacity 261.0 gal., usable fuel 256.0 gal.
Auxiliary (option) 66.0 gal. total usable 322.0 gal.
Total undrainable 10.7 lbs. (without auxiliary option)
total undrainable 13.0 lbs. (with auxiliary option)

Oil capacity 24.0 qts. total (12.0 qts. each engine, 9.0 qts. usable - (See NOTE 1 for
system oil) (+188)
Auxiliary with optional fuel 27.2 qts. total (13.6 qts. each engine,
10.6 qts. usable) (+188)

Control surface movements Elevator Up 30° + 1 Down 10° ± 2

-0 0
Elevator tab Up 6 1/2° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flaps Down 40° ± 2
Aileron tab Up 17° ± 2.5° Down 17° ± 2.5°

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates and approve design and production changes
on airplane serial numbers 685-12000 through 12066. (See NOTES 15 and 22
for serial number variations and SW-2 status.)
2A4 20

XIV - MODEL 690A, 11 PCLM (Normal Category), Approved April 25, 1973

Engines 2 AiResearch Model TPE-331-5-251K Turboprop engines (Rockwell P/N 610495)

Fuel Aviation turbine fuels ASTM designation D1655-68, Types Jet A, Jet B, and
Jet A-1; and MIL-T-5624G(1), Grades JP-4 & JP-5. (See Rockwell Service
Letter 170H) (See Mfg. Data Part V Approved F/M for List of Approved Fuels)

Oil MIL-L-23699A and MIL-L-7808G.

(See Mfg. Data Part V Approved F/M for List of Approved Lubricants)

Engine limits HP. R.P.M. I.T.T.

Takeoff 717.5 101% 923°C
Maximum continuous 717.5 101% 923°C

Propeller and Propeller 2 Hartzell 3-bladed feathering and reversing propellers.

Limits Rockwell Assembly No. 640053.
a. HC-B3TN-5FL Hubs with LT10282H-4 or LT10282H(B)+4 or LT10282+4 or
LT10282(B)+4 or LT10282+4 or LT10282AB+4 blades
OR HC-B3TN-5DL or HC-B3TN-5NL hubs with LT10282A+4 or LT10282AB+4
blades.
Pitch settings at 30 in. Station: Low 13.5° ± 0.2°
Feather 90.0° ± 0.5°, Reverse -8.0° ± 0.5°
Start Locks +2.5° ± 0.2°
Diameter: 106 in, 1/2 in. reduction per blade allowed.
NOTE: Use AiResearch oil transfer tube No. 866533-3.
(See NOTE 16 for alternate blades.)
b. Spinner: 2 Hartzell 836-57P
c. Governor: 2 AiResearch 895490-1 or 895490-3

Airspeed Limits Maneuvering 167 m.p.h. (145K) CAS

Maximum Operating 280 m.p.h. (243K) CAS .52 MACH
Flaps extended - half 207 m.p.h. (180K) CAS
Flaps extended - full 161 m.p.h. (140K) CAS
Landing gear extended 230 m.p.h. (200K) CAS

C.G. Range Forward

212.93 inches aft of datum (22.72% MAC) at 10,250 lbs.
203.75 inches aft of datum (10.40% MAC) at 7,500 lbs.
203.75 inches aft of datum (10.40% MAC) at 6,749 lbs.
214.58 inches aft of datum (24.93% MAC) at 6,000 lbs.
Straight line variation between points
Aft
218.70 inches aft of datum (30.47% MAC) at 10,250 lbs.
217.98 inches aft of datum (29.50% MAC) at 6,278 lbs.
Variation between points:
Inches aft of datum = 219.84 - (11653/Weight)

Datum 196 in forward of wing leading edge at center section

Leveling means Longitudinal - top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of rear baggage compartment floor.

Maximum weight Maximum takeoff 10,250 lbs. (ramp weight 10,300 lbs.)
Maximum landing 9600 lbs.
Zero fuel 8750 lbs.

Maximum operating altitude 31,000 feet

Maximum No. of seats 11 (Pilot +10 passengers; pilot, co-pilot + 9 passengers)

 21 2A4

XIV - MODEL 690A (cont’d)

Maximum baggage 600 lb. (+260)

Fuel capacity Total capacity 389.0 gal., usable fuel 384.0 gal.
(See NOTE 1 for system fuel)

Oil capacity 12.0 qts. total (6.0 qts. total each tank) (+188)
10.0 qts. usable (See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 6 1/2° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flaps Down 40° ± 2
Aileron tab Up 17° ± 2.5° Down 17° ± 2.5°

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates and approve design and production changes
on airplane serial numbers 690A-11100 through 11349. (See NOTES 15 and 22
for serial number variations and SW-2 status.)

XV - MODEL 690B, 10 PCLM (Normal Category), Approved October 5, 1976

Engines 2 AiResearch Model TPE-331-5-251K Turboprop engines (Rockwell P/N 610495),

S/N 11350 through 11542
2 AiResearch Model TPE-331-5-252K Turboprop engines (Rockwell P/N 610495),
S/N 11431, S/N 11543 and subs.

Fuel Aviation turbine fuels ASTM designation D1655-68, Types Jet A, Jet B, and
Jet A-1; and MIL-T-5624G(1), Grades JP-4 & JP-5. (See Rockwell Services
Letter 170H) (See Mfg. Data Part V Approved F/M for List of Approved Fuels).

Oil MIL-L-23699A and MIL-L-7808G (See Mfg. Data Part V Approved F/M for List of
Approved Lubricants).

Engine limits HP. R.P.M. I.T.T.

Takeoff 717.5 101% 923°C
Maximum continuous 717.5 101% 923°C

Propeller and Propeller 2 Hartzell 3-bladed feathering and reversing propellers.

Limits Rockwell Assembly No. 640053.
a. HC-B3TN-5FL Hubs with LT10282H-4 or LT10282H(B)+4 or LT10282+4 or
LT10282(B)+4 or LT10282+4 or LT10282AB+4 blades
OR HC-B3TN-5DL or HC-B3TN-5NL hubs with LT10282A+4 or LT10282AB+4
blades.
Pitch settings at 30 in. Station: Low 13.5° ± 0.2°
Feather 90.0° ± 0.5°, Reverse -8.0° ± 0.5°
Start Locks +2.5° ± 0.2°
Diameter: 106 in, 1/2 in. reduction per blade allowed.
NOTE: Use AiResearch oil transfer tube No. 866533-3.
(See NOTE 16 for alternate blades.)
b. Spinner: 2 Hartzell 836-57P
c. Governor: 2 AiResearch 895490-1 or 895490-3 (for aircraft with
TPE 331-5-251K engines)
2 AiResearch 895490-5 (for aircraft with TPE 331-5-252K engines)
2A4 22

XV - MODEL 690B (cont’d)

Airspeed Limits Maneuvering 171 m.p.h. (149K) CAS
Maximum Operating 280 m.p.h. (243K) CAS .52 MACH
Flaps extended - half 207 m.p.h. (180K) CAS
Flaps extended - full 161 m.p.h. (140K) CAS
Landing gear extended 230 m.p.h. (200K) CAS

C.G. Range Forward

213.14 inches aft of datum (23.00% MAC) at 10,325 lbs.
203.75 inches aft of datum (10,40% MAC) at 7,500 lbs.
203.75 inches aft of datum (10.40% MAC) at 6,749 lbs.
214.58 inches aft of datum (24.93% MAC) at 6,000 lbs.
Straight line variation between points.
Aft
218.64 inches aft of datum (30.39% MAC) at 10,325 lbs.
217.85 inches aft of datum (29.33% MAC) at 6,267 lbs.
Variation between points.
Inches aft of datum = 219.84 - (12444/Weight)

Datum 196 in. forward of wing leading edge at center section.

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of rear baggage compartment floor.

Maximum weight Maximum takeoff 10,325 lbs. (ramp weight 10,375 lbs.)
Maximum landing 9675 lbs.
Zero fuel 8750 lbs.

Maximum operating altitude 31,000 feet

Maximum No. of seats 10 (Pilot + 9 passengers; pilot, co-pilot + 8 passengers)

Maximum baggage 600 lb. (+260)

Fuel capacity Total capacity 389.0 gal., usable fuel 384.0 gal.
(See NOTE 1 for systems fuel)

Oil capacity 12.0 qts. total (6.0 qts. total each tank) (+188)
10.0 qts. usable (See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 6 1/2° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 26° + 2 Left 26° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flaps Down 40° ± 2
Aileron tab Up 17° ± 2.5° Down 17° ± 2.5°

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates and approve design and production changes
on airplane serial numbers 690B-11350 through 11566. (See NOTES 15 and 22
for serial number variations and SW-2 status.)
 23 2A4

XVI - MODEL 690C, 11 PCLM (Normal Category), Approved September 7, 1979

Engines 2 AiResearch Model TPE-331-5-254K Turboprop engines (Rockwell P/N 610495).

Fuel Aviation turbine fuels ASTM designation D1655-68, Types Jet A, Jet A-1, and
Jet B; MIL-T-5624G-1, Grades JP-4 and JP-5; MIL-T-83133, Grade JP-8 and
MIL-F-46005A(MR)-1, Types I and II.

Oil MIL-L-23699B Type II, MIL-L-7808G Type I (See Mfg. Data Part VIII Approved
POH for List of Approved Lubricants).

Engine limits HP. R.P.M. I.T.T.

Takeoff 717.5 101% 923°C
Maximum continuous 717.5 101% 923°C

Propeller and Propeller 2 Dowty-Rotol Ltd. 3-bladed feathering and reversing propellers.
Limits Rockwell Assembly No. 640080.
a. Dowty-Rotol Ltd. Type No. (C) R306/3-82-F/7-(c) VP2926 includes
B. F. Goodrich propeller de-icing kit No. 65-330-1 or Dowty Rotol
Ltd. Type No. (C) R306/3-82-F/7-(c) VP 3027 includes Dowty Rotol
Drice Boots 660709275 as B. F. Goodrich De-Ice Boots 4E 2598-10.
See NOTE 17 for electrical requirements.
Dowty-Rotol Propeller Blade Assembly P/N 660706330-XX
Pitch settings at .7 radius station:
Feather 83 10’ ± 20”, Reverse -13.75° ± 1.0°
Start Locks -1.25° ± 1.0°, Flight Idle 6.0° ± 0.5°
Diameter: 106 in., 1/2 in. reduction per blade allowed.
NOTE: Use AiResearch oil transfer tube No. 897458-2.
NOTE: All engine ground running for maintenance test purposes with the airplane
stationary, must be done with the airplane headed into the wind.
b. Spinner: 2 Dowty-Rotol Ltd. Type No. (C)SB7/3/1
c. Governor: 2 AiResearch P/N 895490-5, 897410-2B, or 897410-4

Airspeed Limits Maneuvering 158 m.p.h. (137K) CAS

Maximum Operating 280 m.p.h. (234K) CAS .52 MACH
Flaps extended - half 207 m.p.h. (180K) CAS (S/N 11600-11729)
230 m.p.h. (200K) CAS (S/N 11730-11999)
Flaps extended - full 161 m.p.h. (140K) CAS (S/N 11600-11729)
184 m.p.h. (160K) CAS (S/N 11730-11999)
Landing gear extended 230 m.p.h. (200K) CAS

C.G. Range Forward

210.51 inches aft of datum (20.06% MAC) at 10,325 lbs.
204.70 inches aft of datum (12.03% MAC) at 7,500 lbs.
204.70 inches aft of datum (12.03% MAC) at 6,798 lbs.
215.10 inches aft of datum (26.42% MAC) at 6,240 lbs.
Straight line variation between points.
Aft
218.67 inches aft of datum (31.35% MAC) at 10,325 lbs.
217.88 inches aft of datum (30.25% MAC) at 6,332 lbs.
Variation between points:
Inches aft of datum = 219.93 - (13029/Weight)

Datum 196 in. forward of wing leading edge at center section

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of rear baggage compartment floor.

Maximum weight Maximum takeoff 10,325 lbs. (ramp weight 10,375 lbs.)
Maximum landing 9675 lbs.
Zero fuel 8800 lbs.
2A4 24

XVI - MODEL 690C (cont’d)

Maximum operating altitude 31,000 feet

Maximum No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers)

Maximum baggage 600 lb. (+260)

Fuel capacity Total standard capacity 430 gal., usable 425 gal.
Total capacity with optional system 482 gal., usable 474 gal.
(See NOTE 1 for systems fuel.)

Oil capacity 12.0 qts. total (6.0 qts. total each tank) (+188)
10.0 qts. usable (See NOTE 1 for system oil)

Control surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 3° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 20° + 2 Left 20° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flaps Down 40° ± 2
Aileron tab Up 17° ± 2.5° Down 17° ± 2.5°

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates and approve design and production changes
on airplane serial numbers 11600 through 11735. (See NOTE 22 for SW-2 status.)

XVII - MODEL 695, 11 PCLM (Normal Category), Approved November 1, 1979

Engines 2 AiResearch Model TPE-331-10-501K Turboprop Engines (Rockwell P/N 610653)
or 2 Garrett Model TPE-331-10-511K Turboprop Engines (Gulfstream P/N 610653)
See NOTE 19 for installation eligibility.

Fuel Aviation turbine fuel ASTM designation D1655-68, Types Jet A and Jet A-1,
and Jet B; MIL-T-5624G-1, Grades JP-4 and JP-5; MIL-T-83133, Grade JP-8,
MIL-F-46005A(MR)-1, Types I and II.

Oil MIL-L-23699B Type II, MIL-L-7808G Type I (See Mfg. Data Part VIII Approved
POH for List of Approved Lubricants).

Engine Limits HP R.P.M. E.G.T.

Takeoff 733 101% 650°C
Maximum continuous 733 101% 650°C

Propeller and Propeller 2 Dowty-Rotol Ltd. 3-bladed feathering and reversing propellers.
Limits Rockwell Assembly No. 640080.
a. Dowty-Rotol Ltd. Type No. (C) R306/3-82-F/7-(c) VP2926 includes
B. F. Goodrich propeller de-icing kit No. 65-330-1 or Dowty Rotol Ltd. Type No.
(C) R306/3-82-F/7-(c) VP 3027 includes Dowty Rotol Deice Boots 660709275 as
B. F. Goodrich De-Ice Boots 4E 2598-10. See NOTE 17 for electrical requirements.
Dowty-Rotol Propeller Blade Assembly P/N 660706330-XX
Pitch settings at .7 radius station:
Feather 83 10’ ± 20’, Reverse -13.75° ± 1.0°,
Start Locks -1.25° ± 1.0°, Flight Idle 6.0° ± 0.5°.
Diameter: 106 in., 1/2 in. reduction per blade allowed.
NOTE: Use AiResearch oil transfer tube Part No. 897458-2.
NOTE: Downwind ground operation above taxi power is prohibited when
airplane is stationary.
 25 2A4

XVII - MODEL 695 (cont’d)

Propeller and Propeller Limits b. Spinner: 2 Dowty-Rotol Ltd. Type No. (C)SB7/3/1
(cont’d) c. Governor: 2 AiResearch P/N 897410-2B or 897410-4.

Airspeed Limits Maneuvering 158 m.p.h. (137K) CAS

Maximum Operating 280 m.p.h. (143K) CAS .52 MACH
Flaps extended - half 207 m.p.h. (180K) CAS
Flaps extended - full 161 m.p.h. (140k) CAS
Landing gear extended 230 m.p.h. (200K) CAS

C.G. Range Forward

210.51 inches aft of datum (20.06% MAC) at 10,325 lbs.
204.70 inches aft of datum (12.03% MAC) at 7,500 lbs.
204.70 inches aft of datum (12.03% MAC) at 6,798 lbs.
215.10 inches aft of datum (26.42% MAC) at 6,240 lbs.
Straight line variation between points.
Aft
218.67 inches aft of datum (31.35% MAC) at 10,325 lbs.
217.88 inches aft of datum (30.25% MAC) at 6,332 lbs.
Variation between points:
Inches aft of datum = 219.93 - (13029/Weight)

Datum 196 in. forward of wing leading edge at center section

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of rear baggage compartment floor.

Maximum weight Maximum takeoff 10,325 lbs. (ramp weight 10,375 lbs.)
Maximum landing 9,675 lbs.
Zero fuel 8,800 lbs.

Maximum operating altitude 31,000 feet

Maximum No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers)

Maximum baggage 600 lb. (+260)

Fuel capacity Total standard capacity 430 gal., usable 425 gal. (S/N 95000 thru 95040).
Total standard capacity 482 gal., usable 474 gal. (S/N 95041 thru 95999).
(See NOTE 1 for systems fuel.)

Oil capacity 12.0 qts. total (6.0 qts. total each tank) (+188)
10.0 qts. usable (See NOTE 1 for system oil).

Control Surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 3° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 20° + 2 Left 20° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flaps Down 40° ± 2
Aileron tab Up 17° ± 2.5° Down 17° ± 2.5°

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates and approve design and production changes
on airplane serial numbers 95000 through 95084. (See NOTE 22 for SW-2 status.)
2A4 26

XVIII - MODEL 695A, 11 PCLM (Normal Category), Approved April 30, 1981

Engines 2 AiResearch Model TPE-331-10-501K Turboprop Engines (Rockwell P/N 610653)

or 2 Garrett Model TPE-331-10-511K Turboprop Engines (Gulfstream P/N 610653)
See NOTE 19 for installation eligibility.

Fuel Aviation turbine fuels ASTM designation D1655-68, Types Jet A, Jet A-1,
and Jet B; MIL-T-5624G-1, Grades JP-4 and JP-5; MIL-T-83133, Grade
JP-8, and MIL-F-46005A(MR)-1, Types I and II.

Oil MIL-L-23699B Type II (See Mfg. Data Part VIII Approved POH for List of
Approved Lubricants).

Engine Limits Torque RPM EGT

Takeoff and
Maximum continuous 102.5%(820) 101.0% 650°C

Propeller and Propeller 2 Dowty-Rotol Ltd. 3-bladed feathering and reversing propellers.
Limits Rockwell Assembly No. 640080.
a. Dowty-Rotol Ltd. Type No. (C) R306/3-82-F/7-(c) VP2926 includes
B. F. Goodrich propeller de-icing kit No. 65-330-1 or Dowty Rotol
Ltd. Type No. (C) R306/3-82-F/7-(c) VP 3027 includes Dowty Rotol
Deice Boots 660709275 as B. F. Goodrich De-Ice Boots 4E 2598-10.
See NOTE 17 for electrical requirements.
Dowty-Rotol Propeller Blade Assembly P/N 660706330-XX
Pitch settings at .7 radius station:
Feather 83 10’ ± 20’, Reverse -13.75° ± 1.0°,
Start Locks -1.25° ± 1.0°, Flight Idle 6.0° ± 0.5°.
Diameter: 106 in., 1/2in. reduction per blade allowed.
NOTE: Use AiResearch oil transfer tube Part No. 897458-2.
NOTE: Downwind ground operation above taxi power is prohibited when airplane
is stationary, must be done with the airplane headed into the wind.
b. Spinner: 2 Dowty-Rotol Ltd. Type No. (C)SB7/3/1
c. Governor: 2 AiResearch P/N 897410-2B or 897410-4.

Airspeed Limits Maneuvering 162 m.p.h. (141K) CAS

Maximum Operating 290 m.p.h. (252K) CAS .60 MACH
Flaps extended - half 207 m.p.h. (180K) CAS (S/N 96000-96055)
230 m.p.h. (200K) CAS (S/N 96056-96999)
Flaps extended- full 161 m.p.h. (140K) CAS (S/N 96000-96055)
184 m.p.h. (160K) CAS (S/N 96056-96999)
Landing gear extended 230 m.p.h. (200K) CAS

C.G. Range Forward

209.78 inches aft of datum (19.1% MAC) at 11,200 lbs.
204.34 inches aft of datum (11.5% MAC) at 8,500 lbs.
204.34 inches aft of datum (11.5% MAC) at 7,010 lbs.
214.18 inches aft of datum (25.1% MAC) at 6,466 lbs.
Straight line variation between points
Aft
218.77 inches aft of datum (31.5% MAC) at 11,200 lbs.
217.95 inches aft of datum (30.4% MAC) at 6,582 lbs.
Variation between points:
Inches aft of datum = 219.93 - (13029/Weight)

Datum 196 in forward of wing leading edge at center section.

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of rear baggage compartment floor.
 27 2A4

XVIII - MODEL 695A (cont’d)

Maximum weight Maximum takeoff 11,200 lbs. (ramp weight 11,250 lbs.)
Maximum landing 10,550 lbs.
Zero fuel 9,500 lbs.

Maximum operating altitude 35,000 feet

Maximum No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers)

Maximum baggage 600 lb. (+290) Non pressurized compartment (See NOTE 18 for exception)
100 lb. (+245) Pressurized compartment

Fuel capacity Total standard capacity 482 gal., usable 474 gal.
(See NOTE 1 for systems fuel)

Oil capacity 12.0 qts. total (6.0 qts. total each tank) (+188)
10.0 qts. usable (See NOTE 1 for system oil)

Control Surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 3° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 20° + 2 Left 20° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flaps Down 40° ± 2
Aileron tab Up 17° ± 2.5° Down 17° ± 2.5°

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates and approve design and production changes
on airplane serial numbers 96000 through 96100. (See NOTES 21 and 22
for model conversion and SW-2 status.)

XIX - MODEL 690D, 11 PCLM (Normal Category) Approved December 2, 1981

Engines 2 AiResearch Model TPE 331-5-254K Turboprop Engines (Gulfstream P/N 610495).

Fuel Aviation turbine fuels ASTM designation D1655-68, types Jet A, Jet A-1 and
Jet B; MIL-T-5624G-1, Grades JP-4 and JP-5; MIL-T-83133, Grade JP-8 and
MIL-F-46005A(MR)-1, Types I and II.

Oil MIL-L-23699B Type II or MIL-L-7808G type I (See Mfg. Data Part VIII Approved
POH for List of Approved Lubricants).

Engine limits HP R.P.M. ITT

Takeoff and 748 101.0% 923°
Maximum continuous

Propeller and Propeller 2 Dowty-Rotol Ltd. 3-bladed feathering and reversing propellers.
Limits Rockwell Assembly No. 640080.
a. Dowty-Rotol Ltd. Type No. (C) R306/3-82-F/7-(c) VP2926 includes
B. F. Goodrich propeller de-icing kit No. 65-330-1 or Dowty Rotol
Ltd. Type No. (C) R306/3-82-F/7-(c) VP 3027 includes Dowty Rotol
Deice Boots 660709275 as B. F. Goodrich De-Ice Boots 4E 2598-10.
See NOTE 17 for electrical requirements.
Dowty-Rotol Propeller Blade Assembly P/N 660706330-XX
Pitch settings at .7 radius station:
2A4 28

XIX - MODEL 690D (cont’d)

Propeller and Propeller Limits Feather 83° 10’ ± 20’, Reverse -13.75° ± 1.0°
(cont’d) Start Locks -1.25° ± 1.0°, Flight Idle 6.0° ± 0.5°.
Diameter: 106 in., 1/2in. reduction per blade allowed.
NOTE: Use AiResearch oil transfer tube Part No. 897458-2.
NOTE: All engine ground running for maintenance test purposes, with the
airplane stationary, must be done with the airplane head into the wind.
b. Spinner: 2 Dowty-Rotol Ltd. Type No. (C)SB7/3/1
c. Governor: 2 AiResearch P/N 897410-2B or -4.

Airspeed Limits Maneuvering 160 m.p.h. (139K) CAS

Maximum Operating 290 m.p.h. (252K) CAS .60 MACH
Flaps extended - half 207 m.p.h. (180K) CAS (S/N 15000-15024)
230 m.p.h. (200K) CAS (S/N 15025-15999)
Flaps extended - full 161 m.p.h. (140K) CAS (S/N 15000-15024)
184 m.p.h. (160K) CAS (S/N 15025-15999)
landing gear extended 230 m.p.h. (200K) CAS

C.G. Range Forward

208.77 inches aft of datum (17.7% MAC) at 10,700 lbs.
204.34 inches aft of datum (11.5% MAC) at 8,500 lbs.
204.34 inches aft of datum (11.5% MAC) at 7,010 lbs.
214.18 inches aft of datum (25.1% MAC) at 6,466 lbs.
Straight line variation between points.
Aft
218.72 inches aft of datum (31.4% MAC) at 10,700 lbs.
217.94 inches aft of datum (30.4% MAC) at 6,582 lbs.
Variation between points
Inches aft of datum = 219.93 - (13029/Weight)

Datum 196 in. forward of wing leading edge at center section

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of rear baggage compartment floor.

Maximum weight Maximum takeoff 10,700 lbs. (ramp weight 10,775 lbs.)
Maximum landing 10,550 lbs.
Zero fuel 9,500 lbs.

Maximum operating altitude 31,000 feet (see NOTE 23 for modification to increase to 35,000 feet)

Maximum No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers)

Maximum baggage 600 lb. (+290) Non pressurized compartment

100 lb. (+245) Pressurized compartment

Fuel capacity Total standard capacity 430 gal., usable fuel 425.0 gal.
Total capacity with optional system 482 gal., usable 474 gal.
(See NOTE 1 for systems fuel).

Oil capacity 12.0 qts. total (6.0 qts. total each tank) (+188)
10.0 qts. usable (See NOTE 1 for system oil)
 29 2A4

XIX - MODEL 690D (cont’d)

Control Surface movements Elevator Up 30° + 1 Down 10° + 2
-0 -0
Elevator tab Up 3° ± 1 Down 24° ± 1
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 20° + 2 Left 20° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flaps Down 40° ± 2
Aileron tab Up 17° ± 2.5° Down 17° ± 2.5°

Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates and approve design and production changes
on airplane serial numbers 15000 through 15042. (See NOTES 21 and 22
for model conversion and SW-2 status.)

XX - MODEL 695B, 11 PCLM (Normal Category), Approved February 15, 1984

Engines 2 Garrett Model TPE 331-10-511K Turboprop engines (Gulfstream P/N 610653).

Fuel Aviation Turbine fuels ASTM designation D1655-68, types Jet A, Jet A-1, and
Jet B; MIL-T-5624G-1, Grades JP-4 and JP-5; MIL-T-83133, Grade JP-8; and
MIL-F-46005A(MR)-1, Types I and II; British D.ENG.R.D. 2486 Issue 2;
British D.ENG.R.D. 2494 Issue 4; and NATO Equivalents.

Oil MIL-L-23699B type II (See Mfg. Data Part VIII Approved POH for List of
approved lubricants.)

Engine Limits Torque (HP) RPM EGT

Takeoff and
Maximum Continuous 102.5% (820) 101.0% 650°C

Propeller and Propeller 2 Dowty-Rotol Ltd. 3-bladed feathering and reversing propellers.
Limits Gulfstream Assembly No. 640080
a. Dowty-Rotol Ltd. Type No. (C) R306/3-82-F/7-(c) VP 3027 includes
Dowty-Rotol Deice Boots 660709275 or B. F. Goodrich De-ice Boots 4E2498-10.
Dowty-Rotol Propeller Blade Assembly P/N 660706330-XX
Pitch settings at .7 radius stations:
Feather 83° 10’± 20’, Reverse -13.75° ± 1.0°
Start Locks -1.25° ± 1.0°, Flight Idle 6.0° ± 0.5°
Diameter: 106 In., 1/2 in. reduction per blade allowed.
NOTE: Use Garrett oil transfer tube Part No. 897458-2.
NOTE: All engine ground running for maintenance and test purposes, with the
airplane stationary, must be done with the airplane headed into the wind.
b. Spinner: 2 Dowty-Rotol Ltd. Type No. (C) SB7/3/1
c. Governor: 2 Garrett P/N 897410-4

Airspeed Limits Maneuvering 182 m.p.h. (158K) CAS

Maximum Operating 290 m.p.h. (252K) CAS .60 MACH
Flaps extended - half 230 m.p.h. (200K) CAS
Flaps extended - full 184 m.p.h. (160K) CAS
Landing gear extended 230 m.p.h. (200K) CAS
2A4 30

XX - MODEL 695B (cont’d)

C.G. Range Forward
210.91 inches aft of datum (20.6% MAC) at 11,750 lbs.
204.34 inches aft of datum (11.5% MAC) at 8,500 lbs.
204.34 inches aft of datum (11.5% MAC) at 6,836 lbs.
211.56 inches aft of datum (21.5% MAC) at 6,410 lbs.
Straight line variation between points.
Aft
217.03 inches aft of datum (29.1% MAC) at 11,750 lbs.
218.71 inches aft of datum (31.4% MAC) at 11,628 lbs.
217.85 inches aft of datum (30.2% MAC) at 6,639 lbs.
Straight line variation except between 11,628 lbs. and 6,639 lbs.
Inches aft of datum = 219.87 - (13402/weight)

Datum 196 In. forward of wing leading edge at center section

Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge.
Lateral - Transverse beams at front of rear baggage compartment floor.

Maximum Weight Maximum takeoff 11,750 lbs. (Maximum Ramp 11,800 lbs.)
Maximum landing 11,000 lbs.
Zero Fuel 9,800 lbs.

Maximum operating altitude 35,000 feet

Maximum No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers)

Maximum baggage 750 lb. (+290) Nonpressurized compartment

100 lb. (+245) Pressurized compartment

Fuel capacity Total standard capacity 482 gal., usable 474 gal.
(See NOTE 1 for systems fuel).

Oil capacity 12.0 qts. total (6.0 qts. total each tank) (+188)
10.0 qts. usable (See NOTE 1 for system oil).

Control Surface movements Elevator Up 30° + 1 Down 10° + 2

-0 -0
Elevator tab Up 3° + 1 Down 24° ± 1
-0
Rudder Right 20° + 2 Left 20° + 2
-0 -0
Rudder tab Right 20° + 2 Left 20° + 2
-0 -0
Aileron Up 23° ± 2 Down 15° ± 2
Flaps Down 40° ± 2
Aileron tab Up 17° ± 2.5° Down 17° ± 2.5°

Serial Nos. eligible Under the Delegation Option Provisions of Part 21 of the Federal Aviation
Regulations, Delegation Option Manufacturer No. SW-2 is authorized to:
Issue Airworthiness Certificates and approve design and production changes
on airplane Serial Numbers 96201 thru 96208 (See NOTES 20 and 22
for model conversion and SW-2 status).
 31 2A4

Specifications Pertinent to All Models

Certification basis Type Certificate No. 2A4

Application for type certificate April 11, 1955.

Models 680, 680E: CAR 3* effective Nov. 1, 1949, through Amdt. 3-12 dated May 18, 1954.
Model 720: CAR 3 effective Nov. 1, 1949, through Amdt. 3-12 dated May 18, 1954,
and 3.197, 3.395, 3.396 of Amdt. 3-2 dated August 12, 1957.
Models 560, 680F, 680FL: CAR 3 effective May 15, 1956, including Amdts. 3-3 dated May 17,
1958, and 3-4 dated October 6, 1958.
Models 680F (Pressurized) CAR 3 effective May 15, 1956, including 3.197, 3.395, 3.396 of Amd. 3-2
680 FL (Pressurized): dated Aug.12, 1957, and Amdt. 3-3 dated May 17, 1958, and 3-4 dated
October 6, 1958.
Model 680T: CAR 3 effective May 15, 1956, including 3.197, 3.395, 3.396 of
Amdt. 3-2 dated August 12, 1957, and Amdts. 3-3 dated May 17, 1958,
3-4 dated Oct. 6, 1958, Amdt. 3-6 dated Sept.13, 1961, plus Special
Conditions dated April 1, 1965.
Models 680V, 680W, 681: CAR 3 effective May 15, 1956, including 3.197, 3.270, 3.395, 3.396 of
Amdt. 3-2 dated August 12, 1957, and Amdts. 3-3 dated May 17, 1958,
3-4 dated Oct.6, 1958, Amdt. 3-6 dated Sept.13, 1961, plus
Special Conditions dated April 1, 1965.
Models 690, 690A, 690B CAR 3 dated May 15, 1956, including Pars. 3.197, 3.270, 3.395, and
3.396 of Amdt. 3-2 dated Aug.12, 1957, and Amdt. 3-3 dated May 17,
1958, 3-4 dated Oct.6, 1958, 3-6 dated Sept.13, 1961, Par. 23.473,
23.479, 23.481, and 23.483 of FAR 23, Amdt. 23-7 dated Sept.14, 1969,
plus Special Conditions dated April 1, 1965, and August 12, 1970; Docket
#10506
Model 685: CAR 3 dated May 15, 1956, including Pars. 3.197, 3.270, 3.395, and
3.396 of Amdt. 3-2 dated August 12, 1957, and Amdt. 3-3 dated May 17,
1958, 3-4 dated Oct.6, 1958, 3-6 dated Sept. 13, 1961.
Models 690C, 695 CAR 3 dated May 15, 1956, including Pars. 3.197, 3.270, 3.395, and
3.396 of Amdt. 3-2 dated August 12, 1957, and Amdt. 3-3 dated May 17,
1958, 3-4 dated Oct.6, 1958, 3-6 dated Sept. 13, 1961, Pars. 23.473,
23.479, 23.481, and 23.483 of FAR 23, Amdt. 23-7 dated Sept. 14, 1969,
plus Special Conditions dated April 1, 1965, and Aug.12, 1970; Docket
#10506, and FAR 36 dated Dec.1, 1969, through Amdt. 36-6 dated
Jan.24, 1977.
Model 695A, 690D CAR 3 dated May 15, 1956, including Pars. 3.197, 3.270, 3.395, and
3.396 of Amdt. 3-2 dated August 12, 1957, and Amdt. 3-3 dated May 1,
1958, 3-4 dated Oct. 6, 1958, 3-6 dated Sept. 13, 1961, Pars. 23.253,
23.335(b)(4), 23.473, 23.479, 23.481, 23.483, 23.571(a), 23.572(a)(1),
and 23.1505(c) of FAR 23, Amdt. 23-7 dated Sept. 14, 1969,
FAR 23.1303(e)(2) of Amdt. 23-17 dated Feb. 1, 1977, plus special
Conditions dated April 1, 1965, and August 12, 1970, Docket No. 10506,
and FAR 36 dated December 1, 1969, through Amdt. 36-6 dated Jan.24, 1977.
Model 695B CAR 3 dated May 15, 1956, including Pars. 3.395 and 3.396 of Amdt.3-2
dated August 12, 1957, and Amdt. 3-3 dated May 1, 1958, 3-4 dated
Oct. 6, 1958, 3-6 dated Sept.13, 1961, except for Subpart C, plus
Pars. 23.253, 23.1303(e)(2), and 23.1505(c), and Subpart C of FAR 23 as
amended thru Change 17 dated Sept.13, 1982, plus Special Conditions
dated April 1, 1965, and Aug.12, 1970, Docket No. 10506 and FAR 36
dated December 1, 1969, through Amdt. 36-6 dated January 24, 1977.
*Civil Air Regulations Part 3

Production basis Production Certificate No. 203

2A4 32

Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification
Basis) must be installed in the aircraft for certification. This equipment must include a current Airplane
Flight Manual except for Models 690B, 690C, 690D, 695, 695A, and 695B which require a current Pilot’s
Operating Handbook.

In addition, the following item(s) are required:

1. Stall warning system:
Models 560F, 680F, 680F(P), 680FL, 680FLP, 680T, 680W, 681, 690, 685, 690A (through S/N 11268
except 11249) - Gulfstream Dwgs. 850016 and 850195.
Models 690A (11249, 11269 through 11349), 690B - Gulfstream Dwgs. 850016 and 8000644
Model 690C, 690D and 695 - Gulfstream Dwgs. 200036 and 800644.
Model 695A and 695B - Gulfstream Dwgs. 200036, 800644 and 800746.

2. Outside Air Temperature Thermometer

Models 680T, 680V, 680W, 681 - Gulfstream Dwg. 850295
Models 690, 690A, 690B, 690C, 690D, 695, 695A, and 695B - Gulfstream Dwg. 850478.

3. EGT System
Model 685 (with Service Letter 300 installed) Gulfstream Dwg. 890412.

NOTE 1: 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 airworthiness certification and at all times
thereafter (except in the case of air carrier operators having an approved weight control system.)

The certificated empty weight and corresponding center of gravity location must include unusable fuel
(included in total fuel capacity and undrainable oil (included in total oil capacity) as follows:

680-F & 680-FL &

Model 680 680-E 720 680-F Press 680-FL(P)
Fuel 15.5 lb.(+187) 15.5 lb.(+187) 15.5 lb.(+187) 15.5 lb.(+187) 15.5 lb.(+231)
Oil 15.0 lb.(+191) 15.0 lb.(+191) 15.0 lb.(+191) 17.4 lb.(+150) 17.4 lb.(+194)

680W, 681 690, 690A

Model 560-F 680T, 680V 690B 685
Fuel 15.5 lb.(+187) 13 lb. (+231) 31 lb.(+231) 27 lb.(+231)
Oil 17.4 lb.(+191) 6.5 lb.(+188) 4 lb.(+188) 0 lb.(+188)

Model 690C, 690D 695 695A, 695B

(SN 95000-
Standard Std + Optional 95040) (95041-95999)
Fuel 33.5 lb.(+230) 53.6 lb.(+230) 33.6 lb.(+230) 53.6 lb.(+230) 53.6 lb.(+230)
Oil 4.0 lb.(+188) 4.0 lb.(+188) 4.0 lb.(+188) 4.0 lb.(+188) 4.0 lb.(+188)

NOTE 2: The placards specified in the Airplane Flight Manual must be displayed in front of and in clear view of the pilots.

NOTE 3: Serial Numbers 466, 471, 529, and 530 of Military RL-26-D as defined by Aero Commander Dwg. 6100012-A are
eligible as Model 680 airplanes.

NOTE 4: When Lycoming GSO-480-B1A6 engines are installed, the following pertains: The oil cooler outlet gills must be
relocated in accordance with Service Letter No. 62 and oil temperature gage markings changed per Service Letter
No. 63. Engines must be operated in accordance with Airplane Flight Manual.

NOTE 5: An optional pressurized version of the Model 680-F designated “680-F (Pressurized)” was approved June 29, 1962.
This model is a standard 680-F incorporating a factory modification per Aero Commander Dwg. 610021. Note the
special required equipment list and the special equipment column for this modified 680-F in Revision No. 24 or
Service Information SI-118.
 33 2A4

NOTE 6: Model 680FL S/N 1471 and up are manufactured as 8500 lb. gross weight aircraft. Serial Numbers 1261 through
1470 are manufactured as 8000 lb. gross weight aircraft and become 8500 lb. aircraft when modified per Aero
Commander Dwg. 6100028. Serial Number 1441through 1470 were modified per Rockwell Dwg. 6100028 at the
factory.

NOTE 7: The Model 680 is eligible as a Model 680E when modified in accordance with Aero Commander Report G10-163.

NOTE 8: All Model 680T aircraft are to be modified or manufactured per Aero Commander Report G10-227 and are to be
8950 lb. gross weight aircraft.

NOTE 9: The Model 680T is eligible as a Model 680V when modified in accordance with Aero Commander Dwg. 6100034.

NOTE 10: Icing Approval:

a. The Models 680T, 680V, 680W, and 681 may be flown through known icing conditions when equipped in
accordance with Aero Commander Service Letter No. 196.
b. The Model 690 may be flown through known icing conditions when equipped in accordance with Aero
Commander Service Letter No. 241A or Drawing 890338. Flight Manual Supplement 4 dated 6/10/71 is
required.
c. Models 690A and 690B are fully equipped and approved for flight into known icing. See Flight Manual
(Pilots Operating Handbook) for list of required operable equipment. Safe Flight P/N C-01426 and C-01427
required to provide stall warning.
d. Model 690C Serial Numbers 11600 thru 11619 approved for flight into known icing after compliance with
Rockwell Service Letter No. 329. Serial Numbers 11620 and Subs are fully equipped for flight into known
icing. See Pilots Operating Handbook for list of required operable equipment.
e. Model 695, 695A, 695B and690D are fully equipped for flight into known icing. See Pilots Operating
Handbook for list of required operable equipment.

NOTE 11: The Models 680T and 680V may have the AiResearch engines TPE-331-43A installed as a product improvement
item and in accordance with Aero Commander Service Letter No. 208.

NOTE 12: The Models 680T, 680V, 680W, and 681 may have auxiliary fuel tanks installed in accordance with Aero
Commander Drawing 890326. These provide 25.5 usable gals. each side. (51 gal. total) Unusable added is
negligible.

NOTE 13: The Model 685 may be approved for flight into known icing conditions when equipped in accordance with Aero
Commander Service Letter No. 241 or Drawing No. 890338. Flight Manual Supplement 5 dated April 15, 1972, is
required.

NOTE 14: With GTS10-520-K engine installed, 2 Alcor turbine inlet temperature indicators must be installed per Rockwell
Service Letter 300. Flight Manual Revision No. 5.

NOTE 15: In some cases, the serial number contains the basic number plus a dash followed by a second set of numbers. This
second number is a model unit number and the basic serial number applies with or without the second number.
Example as follows: 680FL-1779-148 can be referred to as S/N 1779-148 or by S/N 1779.

NOTE 16: If blades LT10673 or LT10673B are installed per STC SA546GL, propeller blade angles at the 42 inch station are:
Reverse 14.0° ± .5°, Start Locks -8.7° ± .5°; Low 6.0° ± .5°, and Feather 77.9° ± .5°.

NOTE 17: Airframe electrical modifications per 800 788 required when installing Dowty Rotol boots 660709275 or B. F.
Goodrich boots 4E2498-10 in place of previously installed B. F. Goodrich de-ice Kit 65-330-1.

NOTE 18: Maximum Baggage Weight increased to 750 pounds for Model 695A Serial Numbers 96063, 96069, 96075,
96078, and 96085.

NOTE 19: TPE 331-10-501K effective on Models 695 S/N 95000 through 95084, 695A S/N 96001through 96071 except
those complying with Service Information Letter 189. TPE 331-1Q-511K effective on Models 695 S/N 95087 and
Subs. 695A S/N 96000, 96072 and Subs. plus those complying with Service Information Letter 189. It is
acceptable to have one each -501K and -511K engine installed.
2A4 34

NOTE 20: Model 695A Serial Numbers 96062, 96063, 96069, 96075, and 96078, and 96085 are eligible as a Model 695B
when modified in accordance with Gulfstream Aerospace Drawing 100062 Rework EO No. 3 except that the
maximum value of zero fuel weights is limited to 9500 pounds.

NOTE 21: Model 690D airplanes, Serial Numbers 15000 through 15042, are eligible for conversion to Model 695A when
modified in accordance with Gulfstream Drawing 100068.

NOTE 22: Delegation Option Authorization No. SW-2 expired July 17, 1986.

NOTE 23: Model 690D maximum operating altitude may be increased to 35,000 feet through the installation of Twin
Commander Aircraft Corporation Custom Kit No. 149.

...END...