A16EA (airframe).  Revision 15 

The Certification basis of the aircraft is taken from FAR 23 effective February 1, 1965, and Amendments 23-1 through 23-8, Date of Application for Type Certificate, July 2, 1970. Type Certificate No. A16EA issued November 12, 1971.

E-274 (Engine: O-320-E2G) Revision 21

True Flight Holdings, LLC
True Flight Aerospace, LLC. All Rights Reserved.
2950 Madison Highway, Valdosta, Georgia 31601 - (229) 242-6337

FAA approved Airplane dated February 26, 1979, is not required for this aircraft

One each Lycoming O-320-E2G (Carburetor MA-4 SPA with settings 10-5062 or 10-5009.)
(Type Certificate Number E-274)

80/87 minimum grade aviation gasoline

For all operations, 2700 rpm (150 hp)

1. McCauley Model 1C172, Type Certificate Number P-910, (either 1C172/BTM7359 fixed pitch propeller with B-4381 spacer (aluminum) or 1C172/SBTM7359 fixed pitch propeller with B-4425 spacer (steel).
(Note: When steel spacer is installed, an "S" will be stamped in front of the BTM on the propeller hub by the airframe manufacturer.) Static rpm at maximum permissible throttle setting; not over 2375 rpm and not under 2250 rpm. No additional tolerance permitted. Diameter: not over 73 inches, not under 71.5 inches. No additional tolerance permitted.

2. McCauley Model 1C172, Type Certificate Number P-910, (either 1C172/BTM7357 fixed pitch propeller with B-4381 spacer (aluminum) or 1C172/SBTM7357 fixed propeller with B-4425 spacer (steel). (Note: When steel spacer is installed, an "S" will be stamped in front on the BTM on the propeller hub by the airframe manufacturer.) Static rpm at maximum permissible throttle setting: not over 2348 rpm, not under 2250 rpm; no additional tolerance permitted. Diameter: not over 73 inches, not under 71.5 inches. No additional tolerance permitted.

Vne Never exceed 190 mph (165 knots)
Vno Maximum structural cruising 150 mph (130 knots)
Va Maneuvering utility category 122 mph (106 knots)
Va Maneuvering normal category 122 mph (106 knots)
Vfe Flaps extended 120 mph (104 knots)
Canopy partially opened 130 mph (113 knots)

Normal (+87.25) to (+90.1) at 2,200 lbs.
. . . . . . .(+80.00) to (+90.1) at 1,780 lbs.
Utility . .(+82.2) to (+84.5) at 1,850 lbs.
. . . . .  ...(+80.0) to (+84.5) at 1,780 lbs.
Straight line variation between points given.

1,850 lbs. (Utility Category)
2,200 lbs. (Normal Category)

2 at (+90.6)  Note:  This is the forward limit.
2 at (+126.0)

120 lbs. at (+148.0)

340 lbs. at (+116.4)   Note: Rear Seat Folded Down

37 gallons (2 wing tanks) at (+90.9)    (See NOTE 1 in "Data Common to all models" for unusable fuel)

8 quarts at (+32.0) (6 quarts usable) (2 quarts minimum)

Elevator 30° ± 2° up 20° ± 2° down
Rudder 25° ± 2° left 25° ± 2° right
Ailerons 15° + 2-0° up 7.5° + 2½-0° down
Flaps 30° ± 2° down
Elevator Trim Tab 16° ± 2° up 19° ± 2° down

AA5-0001 and up (Normal and Utility Category)

Information with respect to service life limited parts on this Model is contained in the applicable manufacturer's service manual, "Model AA-5, AA-5A, AA-5B, AG-5B Service Manual," Section 3-00, "Service Life Limited Components." Service life limits appearing in this manual may not be changed without FAA Engineering approval. Service life limited parts must be retired in accordance with the following schedule:

Component
Inboard Spar Assembly
Wing Spar Assembly
Wing Outboard Spar assembly
Shoulder Bolt.

Part Number
5102310-501
5201002-501
5201189-501
901044-2,-3

Service Life (Hours)
. . . . . 12,000
. . . . . 12,500
. . . . . 12,500
. . . .  .. 7,250

None. Prior to original certification of each aircraft manufactured subsequent to May 12, 2000, an FAA representative must perform a detailed inspection for workmanship, materials and conformity with the approved technical data and a check of the flight characteristics.