A16EA-AMERICAN GENERAL - Data Pertinent to All Models (Revision 11)
AMERICAN GENERAL AA-5, AA-5A, AA-5B, AG-5B, August 25, 1993
- To read about a specific Type Certificate Data Sheet , click on your choice
- Type Certificate Holder: American General Aircraft Holding Co., Inc.
- 2900 One Liberty Place
1650 Market St.
Philadelphia, PA 19103
- (Here is a listing of available Supplemental Type Certifications I got from Avantex)
Data Pertinent to All Models: This date sheet, which is a part of Type Certificate No. A16EA, prescribes conditions
and limitations under which the product for which the type certificate was issued meets the airworthiness requirements
of the Federal Aviation Regulations.
- Datum: 50.0 inches forward of front face of firewall (wing chord 53.32 inches)
- Leveling Means: Canopy Slide Rail
- Certification Basis: 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.
Production Basis: Licensing agreement between Gulfstream Aerospace Corporation (holder of Type
Certificate No. A16EA) of Savannah, Georgia and American General Aircraft
Corporation (licensee) of Greenville, Mississippi holder of Production Certificate No.
331CE.
Equipment: The basic equipment prescribed in the applicable airworthiness regulations (see Certificate Basis) must be
installed in the airplane for certification. In addition,
- An FAA approved Airplane Fight Manual dated February 26, 1979, is required for the following aircraft:
- Model AA5-A: S/N 0729, 0741, 0745, 0750, 0754, 0766, 0770, 0774, 0791, 0826 and subsequent.
- Model AA-5B: S/N 0973, 0975, 1021,1029, 1088, 1092, 1101, 1103, 1104, 1108 and subsequent.
- Model AG-5B: S/N 10000 and subsequent (Airplane Flight Manual dated September 21, 1990)
this just in,
Airfoils shapes (from James Sleigh, SuperLynx N9559U)
- AA-1 uses a NACA 64-415 airfoil, with a modified leading edge.
- AA-1A (B,C, AA-5A and AA5B) is documented as using the same 64-415
but again noted as having a modified leading edge conic section.
- The GA-7 Cougar is documented as using a NACA 63A415.
- All the GA designs use the same airfoil shape from root to (Sighard F. Hoerner) tip.
Here is the info I have for the AA5A/B taken off an old American Av 1974 dwg.(accuracy ?):
Main wing NACA 64,415 (modified)
- Area (inc fus.) 140.12 sqft
- Flap Area 12.14 sqft deflection +0deg, -45deg
- Aileron Area (inc tabs) 11.82 sqft
- wing incidence 3.5 deg
- wing dihederal 5 deg
- wing twist angle 0deg
- wing taper ratio 1
- aspect ratio 7.1
Horizontal Tail
- airfoil NACA 66,-012
- Stabilizer area 17 sqft
- Elevator Area(inc tabs) 15.41 sqft
- Tab area 3.02 sqft
- Horiz. tail incidence 0 deg
- Horiz. tail dihedral 0 deg
- Horiz tail twist 0 deg
- Horiz Tail taper ratio 1
- Elevator Travel 23deg up 17deg down
- Tab travel 14deg up 30deg down
Vertical Tail
- Airfoil NACA 65,-012 (modified)
- Vert fin area 7.02 sqft
- Rudder Area 4.8 sqft (inc tab)
- Vert tail offset angle 0deg
- Vert Tail sweep angle 13deg 40 min 17 sec (@ 25% cord line)
- Vert tail taper ratio .45
- Rudder travel +/- 25deg
Total aircraft length=264" width= 378.42" vert @tail = 91" with beacon