DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION

TYPE CERTIFICATE DATA SHEET NO.A7PC 
	A7PC
Revision 4
AeroSpace Technologies
N22B
N24A
N22S

March 31, 1989	

This data sheet which is part of type certificate No. A7PC prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations.

Type Certificate Holder 		AeroSpace Technologies of Australia Pty Ltd
				226 Lorimer Street
				Port Melbourne Victoria 3207
				Australia

I - Model N22B (Normal Category), Approved May 20, 1977

Engines 				2 Detroit Diesel Allison Division of General Motors Model 250-B17B or 250-B17C or
				250-B17E. (See NOTE 9 regarding intermixing of engines)
Fuel 				MIL-T-5624 Grade JP-4 or JP-5, ASTM-1655 JET A, JET A-1 or JET B; JP-1 fuel
				conforming to ASTM:D-1655 JET A or JET A-1; Diesel fuel No. 1 conforming to
				ASTM:D-1655 JET A or JET A-1.

Oil				MIL-L-23699 or MIL-L-7808G
				Allison 250-B17 Series Operation and Maintenance Manual, Publication 11W2, lists
				approved brand oils.

Engine Limits 				** 				***
     (B17B, B17C,& B17E)* 		SHP 		Gas 		Power 		Turbine
							Generator 	Turbine 		Outlet
							Speed N1 % 	Speed N2 % 	Temp°C
Takeoff (5 minute)
- 250-B17B 				400 		105 		105 		810 (see Note 10)
- 250-B17C 				420 		105 		105 		810
- 250-B17E 				420 		105 		105		810

Maximum continuous
- 250-B17B 				385 		105 		105		810
- 250-B17C				385 		105 		105 		810
- 250-B17E 				385 		105 		105 		810

*See NOTE 7; **See NOTE 8; ***Normal operations are limited to 100% N2 .

				100% N1 = 50,970 r.p.m.
				100% N2 = 33,290 r.p.m. @ 2,030 propeller r.p.m.

Propellers			 2 Hartzell:	Type HC-A3VF-7 or HC-A3VF-7B
						Blade type V10133 D-11 or V10133 N-11

Propeller limits 			Diameter:	90.63 inches nominal
						88 inches minimum

				Pitch setting at 30-inch station:

				Flight Idle 	6 deg. (nominal)
				Ground Idle 	0 deg. (nominal)
				Reverse 		-13.5 deg. ± .5 deg
				Feather 		85 deg. ± 1 deg

Airspeed limits (CAS) 		Vmo (Max. operating) 		169 knots
				Va (Maneuvering) 		131 knots
				Vfe (Max. flap extended)
					0-20° extension 		120 knots
					20-38° extension 		100 knots
				Vlo (Landing gear operating) 	120 knots
				Vle (Landing gear extended) 	120 knots
				Vmc (Minimum control) 		66.5 knots

C.G. range 			187.5 inches to 199.6 inches aft of datum at 8,000 lbs. or less.
				188.6 inches to 199.6 inches aft of datum at 8,500 lbs.
				Straight line variation between 8,000 lbs. and 8,500 lbs.
				Moment change due to retracting landing gear -4,700 in-lbs.

Datum 				Datum located 171.86 inches forward of wing leading edge.

Leveling: 			Longitudinal - along cabin seat rails.

Maximum weights 		Ramp		8,550 lbs.
				Takeoff 		8,500 lbs.
				Landing 	8,500 lbs.

Maximum zero fuel wt.		8,250 lbs. (all weights above 8,250 lbs. must be in fuel weight).

No. of seats 			15 maximum
				Crew at 115.0 inches aft of datum.
				See loading instructions for passenger loading. Passenger permitted in right-hand crew
				seat when crew door/propeller interlock system (Mod N132) incorporated.

Maximum baggage 		400 lbs. at 50.7 inches aft of datum.
				200 lbs. at 353.7 inches aft of datum (with Option G-44 installed).

Fuel capacity 			274 U.S. gal. total in two interconnected tanks per side.
				268 U.S. gal. usable at 197.5 inches aft. of datum.
				With optional self-sealing tanks (GAF Option G28A):
				268 U.S. gal. total in two interconnected tanks per side.
				263 U.S. gal. usable at 197.5 inches aft of datum.

Oil capacity 			1.8 U.S. gal. drainable per engine at 141.0 inches aft of datum.
				(See NOTE 1)

Maximum operating 		25,000 ft. (except as limited by oxygen system requirements).
  altitude 			12,500 ft. (when autopilot engaged).

Control surface movements 	Wing flaps 		Maximum   38°
				Aileron (flap retracted) 		Up 20° 		Down 20°
				Spoiler (flaps 38°) 		Up 28° 		Down 3°
				Horizontal Stabilizer 		Up 18° 		Down 8°
				    (at trailing edge)
				Horizontal Stabilizer Tab 		Up 27° 		Down 12°
				    (trim wheel at zero position)
				Horizontal Stabilizer Trim 	Up 17° 		Down 6°
				    (stabilizer at neutral position)
				Rudder 				Right 23° 	Left 23°
				Rudder tab 			Right 21° 	Left 21°
				    (trim wheel at neutral position)
				Rudder trim 			Right 15° 	Left 15°
				   (rudder at zero position)

				Detail rigging information contained in GAF Maintenance Manual Pub 12.20 Sec 27.

Serial Nos. eligible 		N22B-5 and subsequent. Military versions, designated by serial numbers with
				suffix "M", are not eligible for civil certification. The Government of Australia,
				Department of Transport Certificate of Airworthiness for Export endorsed as
				noted under "Import Requirements" must be submitted for each individual aircraft for
				which application for U.S. airworthiness certification is made.
				(See NOTE 4)

Equipment 			The basic required equipment as prescribed in the applicable airworthiness regulations
				(see Certification Basis) must be installed in the aircraft for airworthiness certification.
				Government Aircraft Factories List of Basic Equipment N22-6007B identifies all
				required and optional equipment approved by the Australian Department of Transport.
				Copy of document is available from FAA, Northwest Mountain Region, Los Angeles
				Aircraft Certification Office.

In addition, the following items of equipment are required:

1.	Department of Transport Approved Airplane Flight Manuals, GAF Pub. No. 12-28C or GAF Pub.
	No. 12-28F (see NOTE 5). Section 3.35.3 of DOT Approved AFM pertains to flame-out and engine inflight
	restarting procedures. Section 4, Figure 4.11 of DOT Approved AFM pertains to maximum takeoff weight
	versus altitude/temperature.

2. 	Indestructible identification plate Part No. GAF N-00-234 (FAR 45.11).

3. 	Safe Flight Instr. Corp. pre-stall warning detectors P/N 165-5 or GAF pre-stall warning detector
	P/N N-81-723 and Safe Flight Instr. Corp. dual warning unit P/N 284.

4. 	Engine oil shutoff valves, GAF P/N N-50-432 (Ref. GAF Option G240 and modification N376).

5. 	Auxiliary fuel boost pump circuit duplication (Ref. GAF Option G247).

6. 	Fail-safe fuel filler neck assemblies, GAF P/N N-57-318. (Ref GAF Option G250).

7. 	Airspeed indicator with dial markings in accordance with GAF Drawing No. N-03-410 or N-80-442
	(Ref. GAF Option G251B).

8. 	Engine fire detection/warning system installed per GAF dwgs. No. N-60-11. System incorporates
	150D/01-200 fire detector switches, N-81-405 warning indicators and 6/N-81-303 warning test switch.

9.	 Fuel strainers per GAF Dwgs No. N-57-210 (Purolator 7510770 type).

10. 	Crew door/propeller interlock system, GAF Dwg. No. N-81-643 (Ref. GAF Mod. N132). Installation required
	if passenger to be carried in R.H. crew seat.

11. 	Propeller autofeather system, GAF Installation Dwg. No. N-50-387 (Ref. GAF Option G214).

12. 	Alternate cabin vented static source system, GAF Installation Dwg. N-80-474 (Ref. GAF Option G284)
	(For IFR operations).

13. 	Extended circuit breaker panel for cabin mounted circuit breakers for the fire detection system, GAF Dwg.
	N-81-646 (Ref. Modification N218) or GAF Dwg. N-81-600 (Ref. GAF Option G267).

The type design approval also includes the installation of equipment as defined by the manufacturer's designated
option identification numbers. The installation of equipment on a particular aircraft will be shown on the option plate
(P/N SD320) located on the forward face of frame 67.95 in the nose baggage locker of each aircraft which is certified to conform to the type design approval and to be in a condition for safe operation as per "Import Requirements."

The following additional equipment required for compliance with FAR 135, Appendix A, Additional Airworthiness
Standards for 10 or More Passenger Airplane:

1. 	Department of Transport Approved Airplane Flight Manual, GAF pub No. 12.28F and AFM Supplement
	No. R271, Air Taxi and Commercial Operations to FAR Part 135.

2.	Oil low pressure warning system, GAF Installation Dwg. N-81-548 (Ref. GAF Option G213).

3. 	Extra master caution panel, GAF P/N N-80-319 (Ref. GAF Option G135).

4. 	Cabin door-open warning system, GAF Installation Dwg N-81-391 (Ref. GAF Option G38) or GAF Installation
	Dwg N-81-12 (Ref. GAF Modification N9).

5. 	Crew door lock indication and inadvertent opening prevention system, GAF DWG. N-10-537/8 Sheet 5
	(Ref. GAF Modification N240)

6. 	Self-illuminating exit signs, GAF Dwg. N-84-90 (Ref. GAF Option G67A).

7. 	Additional cabin markings and placards.

		GAF DWG. N-00-286 (Ref. Option G257)
		GAF DWG. N-00-289 (Ref. Option G301)
		GAF DWG. N-00-291 (Ref. Option G301)
		GAF DWG. N-00-244 (Ref. GAF Modification N240)
		GAF P/N N-18-579 (Ref. Modification N238) when cockpit/cabin divider (Option G79) is
		incorporated.

8. 	When cockpit/cabin divider (Option G79) is installed, the sliding door lock catch P/N N-18-417 must be
	removed (Ref. GAF Modification N283).

9. 	Approved radio and navigation equipment must be installed in accordance with FAR Part 135.157.
	The following radio and navigation equipment were installed at the time of original certification. Alternative
	equipment may be used as approved by the FAA or the Department of Transport (now CAA).
	King KMA20 Audio (Ref. GAF Option G50B including Modification N16 and N97).
	King KX175B Nav-Comm. (Ref. GAF G51 including Modification N113)
	King KX175B Second Nav-Comm. (Ref. GAF Option G73 including Modification N113).
	King KT76 ATC Transponder (Ref. GAF Option G75).
	Collins MCS107 Slaved Compass (Ref. GAF Option G62).

10.	Additional cabin fire extinguishers must be installed per FAR 135.161.
	The cabin fire extinguisher located under the pilot's seat is provided by the manufacturer and must be
	installed at all times.

II - Model N24A (Normal Category), Approved November 16, 1978

Model N24A is similar to N22B. N24A incorporates a lengthened fuselage and an increase in gross weight.

Engines			2 Detroit Diesel Allison Division of General Motors Model 250-B17B
			or 250-B17C or 250-B17E. (See NOTE 9 regarding intermixing of engines.)

Fuel 			MIL-L-5624 Grade JP-4 or JP-5, ASTM:1655 Jet A, JET A-1 or JET B;
			JP-1 Fuel conforming to ASTM:D-1655 Jet A or Jet A-1; Diesel fuel
			No. 1 conforming to ASTM:D-1655 Jet A or Jet A-1.

Oil 			MIL-L-23699 or MIL-L-7808G

Engine Limits			 	** 				***
	(B17B, B17C,& B17E)*		SHP		Gas 		Power 		Turbine
							Generator 	Turbine 		Outlet
							Speed N1 % 	Speed N2 % 	Temp°C
	Takeoff (5 minute)
	- 250-B17B 			400 		105 		105 		810 (see Note 10)
	- 250-B17C 			420 		105 		105 		810
	- 250-B17E 			420 		105 		105 		810

	Maximum continuous
	- 250-B17B 			385 		105 		105 		810
	- 250-B17C 			385 		105 		105 		810
	- 250-B17E 			385 		105 		105 		810
	*See NOTE 7; **See NOTE 8; ***Normal operations are limited to 100% N 2 .

				100% N1 = 50,970 r.p.m.
				100% N2 = 33,290 r.p.m. @ 2,030 propeller r.p.m.

Propellers 			2 Hartzell 	Hub Type HC-A3VF-7 or HC-A3VF-7B
						Blade type V10133 D-11 or V10133 N-11

Propeller Limits 			Diameter: 	90.63 inches maximum
						88 inches maximum

				Pitch setting at 30 in. station:

				Flight Idle 	6 deg. (nominal)
				Ground Idle 	0 deg. (nominal)
				Reverse 		-13.5 deg. ± .5 deg
				Feather		85 deg. ± 1 deg

Airspeed limits (CAS) 		Vmo (Max. operating) 		162 knots
				Va (Maneuvering) 		134 knots
				Vfe (Max. flap extended)
				    0-10° extension 		120 knots
				    10-38° extension 		106 knots
				Vlo (Landing gear operating) 	120 knots
				Vle (Landing gear extended) 	120 knots
				Vmc (Minimum control) 		66 knots

C.G. range 			215.5 inches to 227.6 inches aft of datum at 7,500 lbs. or less.
				217.5 inches to 227.6 inches aft of datum at 9,400 lbs.
				Straight line variation between 7,500 lbs. and 9,400 lbs.
				Moment change due to retracting landing gear -4,700 in-lbs.

Datum 				Datum located 199.86 inches forward of wing leading edge.

Leveling means 			Longitudinal - along cabin seat rails.
				Lateral - across cabin seat rails.

Maximum weights 		Ramp 9,450 lbs.
				Takeoff 9,400 lbs.
				Landing 9,200 lbs.

Maximum zero fuel wt. 		9,150 lbs. (all weights above 9,150 lbs. must be in fuel weight).

No. of seats 			18 maximum
				Crew at 118.5 inches aft of datum.
				Crew at 116.5 inches aft of datum when crew seats relocated to forward mounting
				alternative (Option R238). See loading instructions for passenger loading. Passenger
				can be carried in right-hand crew seat only when crew door/propeller interlock system
				(Modification N132) fitted.

Maximum baggage 		320 lbs. at 37.7 inches aft of datum.
				200 lbs. at 398.7 inches aft of datum (with Option G-44 installed).

Fuel capacity 			274 U.S. gal. total in two interconnected tanks per side.
				268 U.S. gal. usable in two interconnected tanks per side when optional self-sealing
				tanks fitted (Option G28A).
				268 U.S. gal. usable at 225.5 inches aft of datum.
				263 U.S. gal. usable at 225.5 inches aft of datum when optional self-sealing tanks 				fitted (Option G28A).

Oil capacity 			1.8 U.S. gal. drainable per engine at 169.0 inches aft of datum.
				(See NOTE 1)

Maximum operating 		25,000 ft. (except as limited by oxygen system requirements).
altitude 				12,500 ft. (when autopilot engaged).

Control surface movements 	Wing flaps 			Maximum   38°
				Aileron (flap retracted) 		           	Up 20° 		Down 20°
				Spoiler (flaps 38°) 			Up 28° 		Down 3°
				Horizontal Stabilizer 			Up 16° 		Down 10°
				   (at trailing edge)
				Horizontal Stabilizer Tab 			Up 28.5° 	Down 12°
				   (trim wheel at zero position)
				Horizontal Stabilizer Trim 		Up 18° 		Down 6.5°
				   (stabilizer at neutral position)
				Rudder 					Right 21° 	Left 21°
				Rudder tab 				Right 12° 	Left 12°
				   (trim wheel at neutral position)
				Rudder trim 				Right 15° 	Left 19°
				   (rudder at zero position)

				Detail rigging information contained in GAF Maintenance Manual Pub 12.50.

Serial Nos. eligible 		N24A-42 and subsequent. Military versions, designated by serial numbers with
				suffix "M", are not eligible for civil certification. The Government of Australia,
				Department of Transport Certificate of Airworthiness for Export endorsed as
				noted under "Import Requirements" must be submitted for each individual aircraft for
				which application for U.S. airworthiness certification is made. (See NOTE 4)

Equipment 	The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification 		Basis) must be installed in the aircraft for airworthiness certification. Government Aircraft Factories 		List of Basic Equipment N24A-6007 lists all required and optional equipment approved by the 			Australian Department of Transport. Copy of document is available from FAA, Northwest Mountain 		Region, Aircraft Certification Field Office.
		In addition, the following items of equipment are required:

		1.  Department of Transport Approved Airplane Flight Manuals, GAF Pub. No. 12-58F. Section
		     3.35.3 of DOT Approved AFM pertains to flame-out and engine inflight restarting procedures.
		     Section 4, Figure 4.11 of DOT Approved AFM pertains to maximum takeoff weight
		     versus altitude/temperature.

		2.  Indestructible identification plate Part No. GAF N-00-234 (FAR 45.11).

		3.  Safe Flight Instrument Corporation pre-stall warning detectors P/N 165-5 or GAF pre-stall
		     warning detector P/N N-81-723 and Safe Flight Instr. Corp. dual warning unit P/N 284.

		4.  Engine oil shutoff valves, GAF P/N N-50-432 (Ref. GAF Option G240-24 and Modification
		     N376).

		5.  Auxiliary fuel boost pump circuit duplication (Ref. GAF Option G247).

		6.  Fail-safe fuel filler neck assemblies, GAF P/N N-57-318. (Ref GAF Option G250).

		7.  Airspeed indicator P/N 4/N-80-442 (Ref. GAF Option G251D).

		8.  Engine fire detection/warning system installed per GAF Dwgs. No. N-81-2009 System incorporates
		     150D/01-200 fire detector switches, N-81-405 warning indicators and 6/N-81-303 warning test  		     switch.

		9.  Fuel strainers per GAF Dwgs No. N-57-2000 (Purolator 7510770 type).

	            10.  Crew door/propeller interlock system, GAF Dwg. No. N-81-2006 (Ref. GAF Mod. N132).
		     Installation required if passenger to be carried in R.H. crew seat.

	            11.  Propeller autofeather system, GAF Installation Dwg. No. N-50- 387 (Ref. GAF Option G214).

	            12.  Alternate cabin vented static source system, GAF Installation Dwg. N-80-474 (Ref. GAF
		     Option G284). (For IFR operations).

	            13.  Extended circuit breaker panel for cabin mounted circuit breakers for the fire detection system,
		    GAF Dwg. N-81-646 (Ref. GAF Modification N218) or GAF Dwg. N-81-600 (Ref. GAF
		    Option G267).

	            14. Engine Intake Cowl (Ref GAF Modification N374).

	            15. Horizontal stabilizer mass balanced trim tabs (Ref GAF Modification N439).

		The type design approval also includes the installation of equipment as defined by the manufacturer's
		designated option identification numbers. The installation of equipment on a particular aircraft will
		be shown on the option\plate (P/N SD320) located on the forward face of frame 67.95 in the nose
		baggage locker of each aircraft which is certified to conform to the type design approval and to be in
		a condition for safe operation as per "Import Requirements."
		The following additional equipment required for compliance with FAR 135, Appendix A, Additional
		Airworthiness Standards for 10 or More Passenger Airplane:

		1. Department of Transport Approved Airplane Flight Manual, GAF Pub No. 12.58F and
		    AFM Supplement No. R272, Air Taxi and Commercial Operations to FAR Part 135.

		2. Oil low pressure warning system, GAF Installation Dwg. N-81-548 (Ref. GAF Option G213).

		3. Extra master caution panel, GAF P/N N-80-319 (Ref. GAF Option G135).

		4. Cabin door-open warning system, GAF Installation Dwg N-81-12 (Ref. GAF Modification N9/24).

		5. Self-illuminating exit signs, GAF Dwg. N-84-90 (Ref. GAF Option G67A).

		6. Additional cabin markings and placards.

		    GAF DWG. N-00-286 (Ref. Option G257)
		    GAF DWG. N-00-289 (Ref. Option G301)
		    GAF DWG. N-00-291 (Ref. Option G301)

		7. Approved radio and navigational equipment must be installed in accordance with FAR Part 135.157.
		
		    The following particular radio and navigation equipment were installed at the time of original 			    certification. Alternative equipment may be used as approved by the FAA or the Department
		    of Transport (now CAA).

		    King KMA20 Audio (Ref. GAF Option G50B)
		    King KX175B Nav-Comm. (Ref. GAF Option G51-24)
		    King KX175B Second Nav-Comm. (Ref. GAF Option G73-24)
		    King K176 ATC Transponder (Ref. GAF Option G75-24)
		    King KCS55A Pictorial Nav. (Ref. GAF Option G231)

		8. Additional cabin fire extinguishers must be installed per FAR 135.161.

		    The cabin fire extinguishers located under the pilot's seat are provided by the manufacturer and must
  		    be installed at all times.

III. Model N22S (Normal Category), approved March 31, 1989

Model N22S similar to N22B. N22S incorporates an increase in gross weight, Model 250-B17E engine, chin mounted
radome, retractable FLIR, reduction in rudder travel and reduction in number of seats to five maximum.

Engines 			2 Allison Gas Turbine Division of General Motors Model 250-B17E.

Fuel 			MIL-T-5624 Grade JP-4 or JP-5; ASTM:D-1655 Jet A, Jet A-1 or Jet B;
			JP-1 Fuel conforming to ASTM:D-1655 Jet A or Jet A-1, Diesel fuel No 1
			conforming to ASTM:D-1655 Jet A or Jet A-1.

			Allison 250-B17 Series Operation and Maintenance Manual, Publication 11W2,
			lists detailed information.

Oil 			MIL-L-23699 or MIL-L-7808G.

			Allison 250-B17 Series Operation and Maintenance Manual, Publication 11W2,
			lists approved brand oils.
Engine Limits 			** 				***
				SHP 		Gas 		Power 		Turbine
						Generator 	Turbine 		Outlet
						Speed N1 % 	Speed N2 % 	Temp°C
Takeoff 				420 		105 		105 		810
Maximum continuous 		420 		105 		105 		810

			*See NOTE 7; **See NOTE 8; ***Normal operations are limited to 100% N2 .
			105% N1 = 53,519 r.p.m.
			102% N2 = 33,956 r.p.m. @ 2,071 propeller r.p.m.

Propellers 		2 Hartzell 	Hub Type HC-A3VF-7 or HC-A3VF-7B
					Blade type V10133 D-11 or V10133 N-11

Propeller Limits 		Diameter: 	90.63 inches maximum
					88 inches maximum

			Pitch setting at 30 in. station:

			Flight Idle 		6 deg. (nominal)
			Ground Idle 		0 deg. (nominal)
			Reverse 			-13/5 deg. ± .5 deg
			Feather			85 deg. ± 1 deg

Airspeed limits (CAS) 	Vmo (Max. operating) 		162 knots
			Va (Maneuvering) 		136 knots
			Vfe (Max. flap extended)
				0-10° extension 		120 knots
				10-38° extension 		106 knots
			Vlo (Landing gear operating) 	120 knots
			Vle (Landing gear extended) 	120 knots
			Vmc (Minimum control)		74 knots

C.G. range 		187.5 inches to 197.11 inches aft of datum at 8,000 lbs. or less.
			188.6 inches to 197.11 inches aft of datum at 8,500 lbs.
			193.6 inches to 197.11 inches aft of datum at 9,100 lbs.
			Straight line variation between 8,000 lbs. and 8,500 lbs. and between
			    8,500 lbs. and 9,100 lbs.
			Moment change due to retracting landing gear -4,700 in-lbs.

Datum 			Datum located 171.86 inches forward of wing leading edge.

Leveling means 		Longitudinal - along cabin seat rails.
			Lateral - across cabin seat rails.

Maximum weights 	Ramp		9,150 lbs.
			Takeoff 		9,100 lbs.
			Landing 	8,500 lbs.

Maximum zero fuel wt. 	8,250 lbs. (all weights above 8,250 lbs. must be in fuel weight).

No. of seats 		5 maximum
			Flight Crew at 112.0 to 115.0 inches aft of datum.
			Sensor operator at 209.0 inches aft of datum.
			Observer 1 at 271.0 inches aft of datum.
			Observer 2/Instructor at 305.0 inches aft of datum.
Fuel capacity 		274 U.S. gal. total in two interconnected tanks per side.
			268 U.S. gal. usable at 197.5 inches aft of datum..
			89 U.S. gal. total in two wing auxiliary tanks, one per side.
			88 U.S. gal. usable at 197.5 inches aft of datum.

Oil capacity 			1.8 U.S. gal. drainable per engine at 141.0 inches aft of datum.

Maximum operating 		25,000 ft. (except as limited by oxygen system requirements).
  altitude 			12,500 ft. (when autopilot engaged).
				20,000 ft. with fuel in auxiliary tanks (except as limited by oxygen system equirements).

Control surface movements 	Wing flaps 		Maximum   38°
				Aileron (flap retracted) 		Up 20° 		Down 20°
				Spoiler (flaps 38°) 		Up 28° 		Down 3°
				Horizontal Stabilizer 		Up 18° 		Down 8°
				   (at trailing edge)
				Horizontal Stabilizer Tab 		Up 27° 		Down 12°
				   (trim wheel at zero position)
				Horizontal Stabilizer Trim 	Up 17° 		Down 6°
				   (stabilizer at neutral position)
				Rudder 				Right 18° 	Left 18°
				Rudder tab 			Right 6° 45 	Left 6° 45 min
				   (trim wheel at neutral position)
				Rudder trim 			Right 27°	Left 27°
				   (rudder at zero position)

				Detail rigging information contained in GAF Maintenance Manual Pub 12.20, Sec 27.

Serial Nos. eligible 		N22B-5 and subsequent. Military versions, designated by serial numbers with
				suffix "M", are not eligible for civil certification. The Government of Australia,
				Department of Transport and Communication Certificate of Airworthiness for
				Export endorsed as noted under "Import Requirements" must be submitted for
				each individual aircraft for which application for U.S. airworthiness certification
				is made. (See NOTE 4)

Equipment	The basic required equipment as prescribed in the applicable airworthiness regulations (see certification
		basis) must be installed in the aircraft for the airworthiness certification. Build standard is defined in
		document R1065 - Searchmaster USCS Basic Aircraft Build (Coordination Option) and includes the
		following mandatory items of equipment required for FAA certification.

		Equipment Required for Compliance with FAR 23 Amendments 1-9
		1. Department of Transport and Communications approved Airplane Flight Manual ASTA
		    Publication No. 12.28 FS Section 3.19 contains flame-out and engine inflight starting
		    procedures and section 5, Figure 5.7, pertains to maximum takeoff weight versus
		    altitude/temperature.

		2. Indestructible identification plate (ref ASTA DWG N-00-234.

		3. Pre-stall warning detectors (Safe Flight Instrument Corp. P/N 165-5) and dual warning
		    unit (Safe Flight Instrument Corp P/N 284) (Ref ASTA Dwgs N-81-383 and N-81-292).

		4. Engine oil shutoff valves ASTA P/N 1/N-50-432 (Ref ASTA Option G240 and modification
		    N376).

		5. Auxiliary fuel boost pump circuit duplication (Ref ASTA Option G247).

		6. Fail-safe fuel filler neck assemblies, Main tanks - ASTA P/N N-58-318 (Ref ASTA Option
		    G250), Auxiliary tanks ASTA P/N N-57-411/412 (Ref ASTA modification N693).
		
		7. Airspeed indicator with dial markings in accordance with ASTA Dwg NO-8-442 (Ref ASTA
		    Option G251G).

		8. Engine fire detection/warning system installed per ASTA Dwgs N-60-11, N-80-442 and N-81-857,
		    System incorporates 150D/01-200 Fire Detector Switches (ref also ASTA Option R632 -Autofeather
		    and Engine Fire Detector Control Panel).

		9. Fuel strainers per ASTA Dwg No N-57-170 (purolator 7510770).

	            10. Propeller autofeather system, ASTA Installation Dwg N-50-387 (Ref ASTA Option G214).

	            11. Alternate cabin vented static source, ASTA Installation Dwg N-80-688 (ref ASTA Option R637).

	            12. Extended circuit breaker panel for cabin mounted circuit breakers for the Fire Detection System,
		    ASTA Dwg N-81-646 (ref ASTA modification N218).

	            13. Engine Intake Cowl (ref. GAF Modification N374).
		    Compliance with engine inlet anti-icing requirements of FAR 23.1093, Amendment 23-9 has
		    been demonstrated for the Model N22S when (GAF) Modification N374 is fitted.

		Equipment Required for Compliance with FAR 23.785 (g) and (h)

		1. Cockpit Seats (Ref ASTA Dwgs N-00-120) are equipped with PACIFIC SCIENTIFIC inertia
		    reel/shoulder harness/belt assemblies Part No. 0106957-01/1101020-2 to MIL-R-8236.

		2. Sensor Operator's Seat is equipped with a PA Safety Equipment N206-A (ECO 1128) inertia
		    reel/shoulder harness/belt assembly comprising American Safety fittings, buckle (H141-A),
		    inertia reel (Part No. 7260111) and webbing to MIL-W-4088 type 24, (Ref ASTA Dwg
		    N-00-930) approved to DOTC ANO 108.42.

		Equipment Required for Compliance with FAR 135 Appendix A
		1. Department of Transport and Communications Approved Flight Manual, ASTA Pub 12.28FS
		    contains FAR 135 performance data.

		2. Oil low pressure warning system, ASTA Installation Dwg. No. N-81-548 (ref ASTA Option G213).

		3. Combined Caution Panel, ASTA P/N N-80-731 (ref ASTA Option R631).

		4. Cabin door-open warning system, ASTA Installation Dwg N-81-12 (ref ASTA Modification N9).

		5. Crew door lock indication and inadvertent opening prevention system, ASTA Dwg N-10-537/8
		    sheet 5 (ref ASTA modification N240).

		6. Self-illuminating exit signs, ASTA Dwg N-84-90 (ref ASTA Option G67A).

		7. Additional cabin markings and placards.
			ASTA Dwgs. N-00-289, N-00-291 (ref ASTA Option G301)
			ASTA Dwgs N-00-244 (ref ASTA modification N240).

		8. The following radio and navigation equipment is installed (ref FAR 135.159: Radio and navigation
		    equipment extended overwater or IFR operations.)
		    a. Collins VHF-22B transceiver (ASTA Option R600)
		    b. Andrea A301-6 Audio/Intercom System (ASTA Option R617)
		    c. Collins VIR-32 Nav. 1 Receiver (ASTA Option R601)
		    d. Collins VIR-32 Nav. 2 Receiver (ASTA Option R630)
		    e. Collins 718U-5 HF system (ASTA Option R598)
		
		9. Fire extinguishers - Graviner P/N HA1002 one mounted behind right crew seat (ref ASTA Dwg
		    N-10-1513, Option R611) one mounted in cabin in front of jockey seat (ref ASTA DWG N-00-930).

DATA COMMON TO ALL MODELS
Certification basis 	FAR 21.29 and FAR 23, effective February 1, 1965, including Amendment 23-1 to
			23-9 inclusive and FAR Part 135 Appendix A, Additional Airworthiness Standards for
			10 or More Passenger Airplanes, including Amendments 135-1 to 135-41 inclusive.
			N22B and N224A are eligible for operations under FAR Part 135 when the required
			additional equipment as listed under "Equipment" is installed. Compliance has also
			been shown with FAR 36 noise requirements and SFAR 27 fuel venting requirements.
			Satisfactory findings under the Noise Control Act of 1972 completed January 21,
			1977. Negative Environmental Declaration prepared February 4, 1977. Certification
			basis established per AFS-100 letter to APC-200, dated April 12, 1976, and letter
			from Manager, Western Aircraft Certification Office to Government Aircraft
			Factories dated August 1, 1986.

			Australian Department of Transport letter 138/23/30 dated December 10, 1970, to
			Government Aircraft Factories relates to performance requirements for turbopropeller
			installation.

			Australian Department of Transport letter 138/23/61 dated January 17, 1975, to
			Government Aircraft Factories relates to certification of ramp weight.

			Compliance with engine inlet anti-icing requirements of FAR 23.1093, Amendment
			23-9 has been demonstrated for all models when (GAF) Modification N374 is fitted.

			Compliance with ice protection requirements has been demonstrated in accordance with
			FAR 23.1419, Amendment 23-9, when deicing equipment is installed in accordance
			with Customer Option G286.

			Date of Application for Type Certificate: October 14, 1975
			Type Certificate No. A7PC issued May 20, 1977 for Model N22B.
			Type Certificate No. A7PC amended November 16, 1978 to add Model N24A.
			Type Certificate No. A7PC amended December 31, 1981 to add Model 250-B17C
			    engine.
			Type Certificate No. A7PC amended March 31, 1989 to add Model N22S, to change
			   ownership of the Type Certificate, and include Model 250-B17E engine.
			   Compliance has been shown with FAR 36-16, dated November 22, 1988.

Import requirements 	To be considered eligible for operation in the United States, each aircraft
			manufactured under this type certification must be accompanied by a certificate of
			airworthiness for export or certifying statement endorsed by the exporting foreign
			civil airworthiness authority which states (in the English language): This aircraft
			conforms to its U.S. type design (type certification number A7PC) and is in a
			condition for safe operation.

			The U.S. airworthiness certification basis for aircraft type certificated under
			FAR Section 21.29 and exported by the country of manufacture is FAR Sections	
			21.183(c) or 21.185(c).

			The U.S. airworthiness certification basis for aircraft type certificated under
			FAR Section 21.29 exported from countries other than the country of manufacture
			(e.g., third party country) is FAR Sections 21.183(d) or 21.183(b).

			The U.S. airworthiness certification basis for the issuance of an airworthiness
			certificate for aircraft type certificated under FAR Section 21.21 and manufactured
			in a foreign country under a licensing arrangement is FAR Sections 21.1839(d) or
			21.183(b).

			Notwithstanding that the FAR referenced in paragraphs (c) and (d) do not
			specifically address or require a foreign civil airworthiness authority certification,
			such certification is the only practical way for an applicant to show, and the
			Federal Aviation Administration (FAA) to find conformity to the FAA-approved
			type design and condition for safe operation.

			Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness
			Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported
			into the United States.

Service Information 	Maintenance/Structural Repair Manual and all Service Bulletins issued by Government
			Aircraft Factories or Aerospace Technologies of Australia Pty Ltd, are approved by
			the Australian Department of Transport and Communications (now CAA) through
			the Manufacturers' Approval. Documents are available from Aerospace Technologies
			of Australia Pty Ltd., 226 Lorimer Street, Port Melbourne, Victoria, 3207, Australia.

NOTES
NOTE 1. 	Current weight and balance report including list of equipment included in the certificated empty weight
		and loading instructions must be in each aircraft at the time of original certification and at all times 		thereafter.

		Loading instructions and the aircraft Empty Weight Balance Statement for each individual aircraft are 		included in the Australian DOT Approved Airplane Flight Manual or Australian DOTC Approved 			Airplane Flight Manual..

		The "Empty Weight" shown in the aircraft Empty Weight Balance Statement includes unusable fuel and
		undrainable oil.

		The "Basic Empty Weight" shown in the aircraft Empty Weight Balance Statement includes unusable 	 	fuel and undrained oil.

NOTE 2. 	All placards listed in the Approved Airplane Flight Manual must be installed in the appropriate 			locations on the aircraft. AFM Figures 2.6, 2.7, and 2.5 specify placards for flight compartment, main 		cabin, and exterior respectively. Each individual aircraft must be identified with a placard which 			specifies approved types of operation; e.g., VFR or IFR, to which the airplane is limited by the 			equipment installed. Operations into known or forecast icing conditions is prohibited. Additional 			placards for optional equipment must be included as required by the Airplane Flight Manual 			Supplements supplied with the particular aircraft.

NOTE 3. 	Information essential for the proper maintenance of the airplane is contained in:

		"Aircraft Maintenance Manual"
		    GAF Publication 	12.20 (Model N22B)
					12.50 (Model N24A)
					12.20 (Model N22S)

		"Aircraft Wiring Manual"
		    GAF Publication 	12.23 (Model N22B)
					12.53 (Model N24A)
					12.23 (Model N22S)

		The following airplane structural components are fatigue critical and must be replaced at the times 			indicated:

			Model N22B:
			Wing strut lower/upper fittings (P/N 1/N-20-641/643)	14,000 hrs.
			Stub wing/strut pick-up fittings (P/N 1/N-11-544/545) 	18,400 hrs.
			Flap inboard control tube assembly (P/N 1/N-45-1139/1140) 	12,000 hrs.
			Stub wing front spar (P/N 1/N-11-473) 			25,000 hrs.

			Model N24A:
			Wing strut lower/upper fittings (P/N 1/N-20-641/643) 	12,000 hrs.
			Stub wing/strut pick-up fittings (P/N 1/N-11-544/545) 	12,400 hrs.
			Flap inboard control tube assembly (P/N 1/N-45-1139/1140) 	12,000 hrs.
			Stub wing front spar (P/N 1/N-11-473) 			25,000 hrs.

			Model N22S
			Wing strut lower/upper fittings (P/N 1/N-20-641-643) 	12,600 hrs.
			Stub wing/strut pickup fittings (P/N 1/N-11-544/545) 	14,100 hrs.
			Flap inboard control tube assy (P/N 1/N-45-1139/1140) 	12,000 hrs.
			Stub wing front spar (P/N 1/N-11-473) 			25,000 hrs.

			These retirement lives may be extended subsequent to the completion of full-scale fatigue
			tests to failure by the manufacturer. Further information and approval for any life
			extension may be obtained from FAA, Northwest Mountain Region, Los Angeles Aircraft
			Certification Office, or as authorized by Australian DOT approved Service Bulletins
			issued by the manufacturer (see "Service Information").

			The engine life limited components and their retirement or TBO hours are as listed in the
			FAA approved Allison 250-B17 series Operations and Maintenance Manual Pub 11W2 issued
			by the engine manufacturer.

NOTE 4. 	Aircraft equipped to comply with the requirements of FAR 23 (see "Certification Basis") will be 			identified by the suffix F to the serial number.

NOTE 5. 	Approved Airplane Flight Manual, GAF Pub. No. 12.28F supersedes GAF Pub. No. 12.28C fitted
		to earlier aircraft.

NOTE 6. 	Loading limitations for Nomad N22B and N24A freighter (all cargo) configurations contained in
		GAF Drawings No. N-00-347 and No. N-00-348 respectively.

NOTE 7. 	The engine limits listed are the N1, N2 and T.O.T. limits and rated SHP as shown in the engine type
		certificate data sheet NO. E10CE, Revision 12, for the Allison Models 250-B17B, 250-B17C, and
		250-B17E engines.

NOTE 8. 	For Models N22B and N24A the airframe manufacturer's installed limits and the performance charts
		in the particular airplane flight manual are based on the engine manufacturer's T.O.T. and torque meter
		limits for the Model 250-B17B engine of 810°C (takeoff and maximum continuous) and 1087 lb. ft.
		(take-off) and 996 lb. ft. (maximum continuous). These limits are equal to or less than the corresponding
		limits for the Model 250-B17C engine.
		
		For Model N22S the airframe manufacturer's installed limits and the performance charts in the airplane
		flight manual are based on the engine manufacturer's T.O.T. limit for the Model 250-B17E engine of
		810°C (take-off and maximum continuous).

NOTE 9. 	This model may intermix with the following engines in the combination and with appropriate 			limitations noted in the Australian Department of Transport Approved Flight Manuals.

NOTE 10. 	The maximum allowable torque as measured by the torquemeter for below standards inlet air
		temperature and/or ram conditions is 1165 lb.-ft. for 10 seconds; 1087 lb.-ft. for takeoff and 996 lb-ft.
		for maximum continuous.

NOTE 11. 	The statement of compliance with FAA Airworthiness Directive is contained in Report No. N22S-6012F
		Nomal Model N22S Certification Compliance with FAA Airworthiness Directives.

.....END.....