DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION

TYPE CERTIFICATE DATA SHEET A6EU	A6EU
Revision 7
NORD-AVIATION
Nord 262A Series

July 2, 1986

This data sheet, which is a part of type certificate No. A6EU, 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: 	AEROSPATIALE (Societe Nationale Industrielle Aerospatiale)
				37, blvd de Montmorency
				75016 Paris, France (formerly Nord-Aviation, S.A.)

I - Nord262A Series (Transport Category), approved March 15, 1965, for Model 262A-12.
     Amended January 10, 1974, to include entire Nord 262A Series.

Engines 				2 Turbomeca Bastan VI Model C-1 (Turboprop)
				Reduction gearing, Engine: Propeller, 21.0909: 1

Fuel (Fuels shall conform 		JP-1
    to the specifications as 		    American JP-1 ASTM Jet A and Jet A1
    listed or to subsequent 		    French TRO Norme AIR 3405
    revisions thereof) 		    British D.Eng.R.D. 2453 - D.Eng.R.D. 2494

				JP-4 (See NOTE 3)
				    American JP-4 MIL-T-5624 and ASTM Jet B
				    French TR4 Norme AIR 3407
				    British D.Eng.R.D. 2486 - D.Eng.R.D. 2454

				Water/Methanol
	`			    Water/Methanol Mixture - 	56% water/ 44% methanol by volume
				    Methanol Specification - 	American OM 232 Grade A
								French AIR 3651
								British D.Eng.R.D. 2491
								NATO S747

				Approved Fuel Additives
				    Phillips PFA/55 MB anti-icing additive in quantity up to 0.15% by volume.
				    Shell ASA-3 antistatic additive in quantity up to 0.0001% by volume.

Oil (Engine and Gearbox) 		American MIL-L-00.7808 and MIL-L-23699*
				French AIR 3513, AIR 3514, AIR 3517* and AIR 3515*
				British D.Eng.R.D. 2490 and D.Eng.R.D. 2487*
				* The oil specifications marked with * should not be used below -30°C

Engine Limits 			Rating (static sea level, ISA)
							Shaft Horsepower 	Jet Thrust 	Engine Speed
							        (shp) 		     (lb.) 		    (r.p.m.)
				  WET Takeoff (5 min.) 	         987 		     180 		     33,500
				  DRY Takeoff and Maximum    987		     180		     33,500
				       Continuous (unrestricted)

Engine Limits (cont’d) 		Engine Temperature Limits
				Turbine Gas Temperature, T4 (Jet Pipe)
				   WET Takeoff (5 min.) 				550°C 	(1022°F)
				   DRY Takeoff and Maximum Continuous 		530°C 	(985°F)
				   Starting (Momentary) 				650°C 	(1202°F)
				Oil Inlet Temperature (measured in tank)
				   Minimum for applying power 			15°C 	(59°F)
				   Minimum in flight (steady conditions) 		25°C 	(77°F)
				   Maximum 					85°C 	(185°F)

				Vibration Maximum Amplitude
				   30 microns (i.e. vibration indicator reading of 1.96 or of 50 percent.) (See NOTE 6)

				Engine Speed Limitations
				   Nominal engine r.p.m. 				99.4% 	(33, 500)
				   Minimum Regulated r.p.m. 			86 % 	(29, 000)
				   Maximum Permissible r.p.m. 			102.6% 	(34, 600)
				   ± 1 percent margin is permissible to allow for tachometer instrument error.

Propeller and Propeller Limits 	2 Ratier-Figeac Model FH-146, with 3 FH.106.200 blades each.
				Diameter 10.49 ft. (nominal)
				   Minimum allowable for repairs 10,392 ft. No further reduction permitted.
				Pitch settings at .7 radius.
				   Ground fine 	-1° 	48’
				   Flight fine 	 9°	54’
				   Feathered 	 81°

Airspeed Limits (IAS)
				VMO (Maximum Operating)					214 kts.
				VFE (flaps down 35°) 						127 kts.
				VFE (flaps down 15°) 						143 kts.
				VLO (landing gear operation) 					143 kts.
				VLE (landing gear extended) 					154 kts.
				VMC Minimum control speed with the critical engine inoperative	  86 kts.
				  (propeller windmilling or auto-feathering) 				(ISA S.L.)
				VA (design maneuvering) 						133 kts.

C.G. Range (Gear Extended)			
	           Forward Limits	                Aft Limits	
	Weight
(lb.)	% Reference
Chord	
Sta.	% Reference
Chord	
Sta.	
Takeoff	23, 370
22, 930	20.9
20.3	312.5
311.4	30.0
30.0	323.6 (See NOTE 4)
323.6	
Landing	20, 280
18, 080	16.0
12.0	306.5
301.9	30.0
30.0	323.6
323.6	

Reference Chord 			The reference chord is the wing root profile chord at the center section = 122 in.
				Stations (sta.) are given in inches linear distance from datum.

Datum 				The datum, or origin of moments, is Station 0 located 3 in. forward of the nose or 287 				in. forward of the leading edge of the center section wing root.

Leveling Means 			Leveling is provided by a bubble level, for both longitudinal and transverse directions,
				located at Fuselage Frame Sta. No. 11, approx. 4 in. below cabin floor. Access is 				gained by removing a floor panel.

Maximum Weights (lb.) 					Model 262A-12 		All Models Except
							(See NOTE 4) 		Model 262A-12
				Ramp 			   23,050 		     23,490
				Takeoff (brake release) 	   22,930 		     23,370
				Landing 			   22,710 		     22,710
				Zero Fuel 		   22,710 		     22,710

Minimum Crew 			2 - Pilot and copilot.

Maximum Passengers 		29 - As limited by approved seating arrangement.

Maximum Baggage
Compartment	Arm
(in.)	Capacity
(lb.)	Max. Floor Loading
(lb./sq. ft)	
Model 262A-12
A. (Fwd L.H.)
B. (Fwd R.H.)
C. (Fwd L.H.) (partial loading)
D. (Rear R.H.)
     (Upper Shelf)
     (Middle Shelf)
     (Lower Shelf)	
169.0
169.0
182.0

530.0
530.0
530.0	
665
720
245

162
148
206
	
100
100
100

15
15
30
	
Model 262A
A. (Fwd L.H.)
B. (Fwd R.H.)
C. (Rear R.H.)
     (Upper Shelf)
     (Middle Shelf)
     (Lower Shelf)	
173.0
169.0

528.0
528.0
528.0
	
660
720
132

132
165
	
85
85
15

15
30

Standard Fuel Capacity 		Two wing tanks, Sta. 344.0, each of 264 U.S. Gal usable. Airplane total usable fuel is
				528 U.S. Gal.

Optional Fuel Capacity 		Two auxiliary fuel tanks, Sta. 344.0, each of 75 U.S. Gal usable. With the auxiliary
				tanks, airplane total fuel is 678 U.S. Gal. (See NOTE 2)
				(See Note 1(c) for system and unusable fuel)

Water/Methanol Capacity 		One tank in R.H. landing fairing, Sta. 307.0, 205 lb. capacity. 28.29 U.S. Gal.

Oil Capacity 			Total system 5.8 U.S. Gal.
				Tank capacity 3.2 U.S. Gal. quantity usable, 8 lb., for each engine located in annular
				tanks mounted in engine nose cowls, Sta. 216.0.

Maximum Altitude 		19, 200 ft.

Other Operating Limitations 	The aircraft must be operated in accordance with the limitations presented in the
				SGAC (Secretariat General a l’Aviation Civile)-Approved Airplane Flight Manual.

Control Surface Movements
Elevator
Elevator trim tab
Elevator balance tab	Up
Up
Up	20°
6°
7°	16’ 
45’ 
17’ 	± 30’
± 1°
± 1°	Down
Down
Down	16°
6°
6°	17’ 
45’ 
30’ 	± 30’
± 1°
± 1°	
Aileron
Aileron trim tab
Aileron balance tab	Up
Up
Up	18°
12°
6°	30’

10’ 	± 30’
± 1°
± 1°	Down
Down
Down	13°
12°
4°	20’ 

27’ 	± 30’
± 1°
± 1°	
Rudder
Rudder trim tab
Rudder balance tab	Right
Right
Right	22°
15°
7°	
40’ 
20’ 	± 30’
± 1°
± 1°	Left
Left
Left	22°
15°
7°	
40’ 
20’ 	± 30’
± 1°
± 1°	
Wing Flaps	Outer	35°			Inner	25°			

Serial Nos. Eligible 		The French Certificate of Airworthiness for Export endorsed as noted under “Import
				Requirements” must be submitted for each individual aircraft for which application for
				standard airworthiness certification is made. (See NOTE 7).

Certification Basis 		CAR Part 10 dated March 1955 and French Specification AIR 2051 as revised to June
				15, 1963, certified by SGAC as equivalent to U.S. CAR Part 4b, effective December 				31, 1953 plus amendments 4b-1 through 4b-14, Special Conditions as stated in FAA 				letters dated November 15, 1963 and January 19, 1964, and Special Regulations SR-				422B effective July 9, 1959. Type Certificate No. A6EU issued March 15, 1965. Date 				of Application for type certificate: April 1, 1962.

				Compliance with the following optional requirements has been established:
				French Spec. AIR 2051 Sections equivalent to:
				    Ditching provisions CAR 4b.361
				    Ice protection provisions CAR 4b.640

Import Requirements 		A United States Certificate of Airworthiness may be issued on the basis of French
				Certificate of Airworthiness for Export signed by a representative of the Secretariat
				General a l’Aviation Civile (SGAC) containing the following statement, “The airplane
				covered by this certificate has been examined and found to comply with French AIR
				2051 Regulation effective June 15, 1963 and conforms to type certificate No. A6EU.”

Required Equipment 		The basic equipment as prescribed in the applicable airworthiness regulations (See
				Certification Basis) must be installed in the aircraft for certification.

				Model numbers of Nord 262 airplanes of the “A” series carry a dash number which
				identifies the particular customer configuration. Such configurations differ from the
				basic 262A type design primarily with regard to optional cockpit equipment and 					interior arrangement.

				NORD AVIATION Report 262 12 00 700 contains a list of required equipment for
				Model 262A-12. Nord Aviation Report 262A 00 700 contains lists of required
				equipment and optional equipment for Model 262A.

				In addition, the following items of equipment are required:

				    Battery Temperature Control Installation, except for Model 262A-12, in accordance
				    with Nord Aviation Modification No. 789 (Service Bulletin No. 26-10).

				    For Model 262A-12, SGAC-approved Airplane Flight Manual, approved March 15,
				    1965, reissued May 31, 1965.

				    For all Models except Model 262A-12, SGAC-approved Airplane Flight Manual 				    for Nord 262A, approved June 10, 1966, reissued January 10, 1974.

Service Information 		Information essential to the proper maintenance of the aircraft, including retirement 				times of parts with a predetermined service life, is included in the Nord-Aviation 				NORD 262A Series Maintenance Manual. Service Bulletins, when approved by 					SGAC, will carry a statement to that effect. The Nord-Aviation Structural Repair 				Manual contains SGAC-approved information.
NOTES
NOTE 1.	(a) A current weight and balance report, including a list of equipment in certificated empty weight and 		      loading instructions, must be provided for each airplane at the time of the original airworthiness 		      certification and at all times thereafter (except in the case of operators having an approved weight 		      control system).
		(b) The airplane must be loaded so that the C.G. is within the specified limits at all times with the effects 		      of fuel usage and movement of crew and passengers from their assigned positions being considered.
		(c) The “drainable unusable” fuel is that amount of fuel in the tanks which is unavailable to the engines 		      under critical flight conditions as defined in French AIR 2051 Regulation 5.16 (CAR 4b.416). This 		      drainable unusable fuel does not include the “tank trapped fuel”. The total unusable fuel must be 		      included in the airplane empty weight or be suitably accounted for in the airplane weight and 			      balance report. The total volume of unusable fuel in U.S. Gal., with or without auxiliary tanks is:

					Airplane Total
					Vol. U.S. Gals. 		Wt. lb. 		Arm. in.
		Tank trapped 		    5.3 			  36 		 343.2
		Drainable unusable 	    0.0 			   0 		     0.0
		Total unusable 		    5.3 			  36 		 343.2

		(d) Engine system oil is the total oil less the quantity drainable from the tank and is the amount of oil 		     normally trapped in the propellers plus the amount normally trapped in the engines after drainage. 		     System oil must be included in empty weight. The undrainable oil in this airplane is negligible.
NOTE 2 	Series 262A airplanes are eligible for operation with the SGAC-approved auxiliary fuel tank installation
		comprised of Nord Aviation Modification Nos. 354, 393, and 394.
NOTE 3 	JP4 fuel, or any mixture of JP4 and JP1, may be used without readjustment of the engine fuel control 		unit. When operating with JP4 fuel, or with any mixture of JP4 and JP1, the performance and operating 		limitations presented for operation with JP4 fuel in Appendix I of the Airplane Flight Manual must be 		observed.
NOTE 4 	Model 262A-12 airplane may be operated at maximum ramp weight of 23, 490 lbs. and maximum 			takeoff weight (brake release) of 23, 370 lbs., in accordance with Airplane Flight Manual Revision No. 		22, dated October 16, 1973. Cockpit placard must be modified in accordance with Nord Aviation N-262 		Modification No. 603.
NOTE 5 	Series 262A airplanes embodying in the enlarged wing tips of SGAC-approved Nord Aviation 			Modification No. 640 (Service Bulletin 57-9) may be operated in accordance with the performance and 		operating limitations presented in Appendix V of the Airplane Flight Manual.
NOTE 6 	Series 262A airplanes may be operated with engine vibration indicators installed in accordance with 		Nord Aviation Modification No. 429/1 (Service Bulletin 77-1) or Modification No. 429/2 (Service 		Bulletin 77-2). If installed, graduation of the indicator must conform with the following:
			Mod. 429/1: Range from 0 to 5, with red radial line at 1.96.
			Mod. 429/2: Range from 0 to 100 percent, with red radial line at 50 percent.
		Series 262A airplanes which incorporate Modification No. 853 (Service Bulletin 77-11) shall be 			operated according to Service Letter 77-10 with engine vibration periodic ground checks to replace 		continuous inflight engine vibration monitoring.
NOTE 7 	SGAC-approved Aerospatiale Report No. DEP/CRA-21/74 (including SGAC (DGAC) approved 			revisions) titled, “Definition of Nord 262A Version for FAA Certification”, identifies modifications 		necessary for conformity with the approved type design of the Nord 262A series. This report also 			identifies mandatory modifications applicable to the intitially certificated -12 version of the aircraft. 		Serial number effectivity of each mandatory modification is specified in the appropriate service bulletin.

							.....END.....