# TCDS A16EA: True Flight Holdings LLC

- Type: Type certificate data sheet
- Status: Current
- Holder: True Flight Holdings LLC
- Revision: 16
- Revised: December 12, 2013
- Product: Aircraft, Small Airplane
- Certification basis: Part 23
- Registered aircraft: 1,889, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/25/b4/25b450a4529f43040656962d17842c4ee5e61220dc9d892d885ddc3237f32c8e
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/9F9B44406EFAB9ED86257C3F0067715E.0001
- Page: https://openairdocs.org/tcds/A16EA

## Models (4)

As the data sheet lists them.

- AA-5B
- AA-5A
- AG-5B
- AA-5

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4 5 6 7 8 9 10 
Rev. No. 16 13 13 13 13 13 15 13 13 13 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 
A16EA 
Revision 16 
 
True Flight Holdings LLC 
AA-5, 
AA-5A, AA-5B 
AG-5B 
 
December 12, 2013 
 
 
TYPE CERTIFICATE DATA SHEET NO. A16EA 
 
This data 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.  
 
Type Certificate Holder: True Flight Holdings LLC 
 2300 Madison Highway 
 Valdosta, GA  31601 
 
Type Certificate Holder Record: American Aviation Corporation transferred TC A16EA to 
Grumman American Aviation Corportation on February 27, 1973 
 
 Grumman American Aviation Corporation transferred TC A16EA to 
Gulfstream American Corporation on September 1, 1978 
 
 Gulfstream American Corporation transferred TC A16EA to 
Gulfstream Aerospace Corporation on November 15, 1982 
 
 Gulfstream Aerospace Corporation transferred TC A16EA to 
American General Aircraft Corporation on October 29, 1992 
 
 American General Aircraft Corporation transferred TC A16EA to 
American General Aircraft Holding Company, Inc. on August 23, 1993 
 
 American General Aircraft Holding Corporation, Inc. transferred TC A16EA 
to Tiger Aircraft LLC on March 22, 2000 
 
 Tiger Aircraft LLC transferred TC A16EA to True Flight Holdings LLC on August 31, 
2007 
 
I. - Model AA5, Traveler, 4 PCLM, Utility Category, approved November 12, 1971; Normal Category, approved November 12, 1971 
 
Engine One each Lycoming O-320-E2G (Carburetor MA-4 SPA with settings 10-5062 or 
10-5009.)  (Type Certificate Number E-274) 
 
Fuel 80/87 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 rpm  (150 hp) 
 
Propeller and Propeller Limits 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; not under  
  2250.  No additional tolerance permitted.  Diameter:  not over 73 inches, not under

A16EA 
Page 2 
 
  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, not under 2250; no additional tolerance 
  permitted.  Diameter:  not over 73 inches, not under 71.5 inches.  No additional 
  tolerance permitted. 
 
Propeller Spinner (Original spinner installation)  Backplate Assembly 5506006-501, Shim 6602035-1, 
Front Bulkhead 5506005-1 or -3 and Spinner 5506001-1 or -510; or (Globe spinner 
installation)  Bulkhead Assembly Aft 5506008-503, Bulkhead Assembly Fwd 5506010-
501, Doubler 5506011-1 and Spinner 5506009-3. 
 
 
Airspeed Limits Vne Never exceed 190 mph (165 knots) 
    (CAS) 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) 
 
C.G. Range Normal (+87.25 to (+90.1) at 2,200 lbs. 
  (+80.0) to (+90.1) at 1,700 lbs. 
 Utility (+82.2) to (+84.5) at  1,850 lbs. 
  (+80.0) to (+84.5) at 1,700 lbs. 
 Straight line variation between points given. 
 
Empty Weight C. G. Range None 
 
Maximum Weight 1,850 lbs.  (Utility Category) 
 2,200 lbs.  (Normal Category) 
 
Number of Seats 2  at (+90.6) 
 2 at (+126.0) 
 
Maximum Baggage 120 lbs. at (+148.0) 
 
Maximum Cargo 
  (Rear Seat Folded Down) 340 lbs. at (+116.4) 
 
Fuel Capacity 37 gallons (2 wing tanks)  at (+90.9) 
    (See NOTE 1 for unusable fuel) 
 
Oil Capacity 8 quarts at (+32.0) (6 quarts usable) 
 (2 quarts minimum) 
 
Control Surface Movements Elevator 30° ± 2° up 20° ± 2° down 
 Rudder 25° ± 2° left 25° ± 2° right 
(Nominal from Neutral) Ailerons 15° + 2-0° up 7.5° + 2½-0° down 
 Flaps   30° ± 2° down 
 Elevator Trim Tab 16° ± 2° up 19° ± 2° down 
 
Serial Numbers Eligible AA5-0001 and up  (Normal and Utility Category) 
 
Service Life Limit 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.

A16EA 
Page 3 
 
 Service life limited parts must be retired in accordance with the following schedule: 
 
 Component Part Number Service Life  (Hours) 
 Inboard Spar Assembly 5102310-501 12,000 
 Wing Spar Assembly 5201002-501 12,500 
 Wing Outboard Spar Assembly 5201189-501 12,500 
 Shoulder Bolt 901044-2,-3   7,250 
 
Production Basis 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. 
 
II. - Model AA-5A, Cheetah, 4 PCLM, Utility Category, approved July 28, 1975; Normal Category, approved  
 July 28, 1975 
Engine One each Lycoming O-320-E2G (Carburetor MA-4 SPA with settings 10-5062 or 
10-5009) (Type Certificate Number E-274) 
 
Fuel 80/87 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2,700 rpm  (150 hp) 
 
Propeller and Propeller Limits 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; not under 2250.  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 pitch 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; not under 2250.  No additional tolerance  
  permitted.  Diameter:  not over 73 inches; not under 71.5 inches.  No  
  additional tolerance permitted. 
 
Airspeed Limits Vne Never exceed 190 mph (165 knots) 
    (CAS) 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) 
 
C.G. Range Normal (+85.60) to (+92.5) at 2,200 lbs. 
  (+81.0) to (+92.5) at 1,780 lbs. 
 Utility (+81.8) to (+86.0) at  1,850 lbs. 
  (+81.0) to (+86.0) at 1,780 lbs. 
 Straight line variation between points given. 
 
Empty Weight C. G. Range None 
 
Maximum Weight 1,850 lbs. (Utility Category) 
 2,200 lbs. (Normal Category) 
 
Number of Seats 2 at (+90.6) 
 2 at (+126.0) 
 
Maximum Baggage 120 lbs. at (+148.0)

A16EA 
Page 4 
 
Maximum Cargo 
  (Rear Seat Folded Down) 340 lbs. at (+116.4) 
 
Fuel Capacity 37 gallons (2 wing tanks)  at  (+90.9) 
  (Standard Tanks) (See NOTE 1 for unusable fuel) 
 
Fuel Capacity 51 gallons (2 wing tanks)  at  (+94.8) 
  (Optional Tanks) (See NOTE 1 for unusable fuel) 
 
Oil Capacity 8 quarts at (+32.0) (6 quarts usable) 
 (2 quarts minimum) 
 
Control Surface Movements Elevator 23° ± 1° up 17° ± 2° down 
  (Nominal from neutral) Rudder 25° ± 2° left 25° ± 2° right 
 Ailerons 15° + 2-0° up 7.5° + 2½-0° down 
 Flaps   45° ± 2° down 
 Elevator Trim Tab 14° ± 3° up 30° ± 1° down 
 
Serial Numbers Eligible AA5A-0001 and up  (Normal and Utility Category) 
 
Service Life Limit 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 (Section 5 after 1976), "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 Part Number Service Life  (Hours) 
 Inboard Spar Assembly 5102310-501 12,000 
 Wing Spar Assembly (Standard) 5201002-501 12,500 
 Wind Spar Assembly (Optional) 5201004-501 12,500 
 Wing Outboard Spar Assembly 5201189-501 12,500 
 Shoulder Bolt 901044-2, -3   7,250 
 
Production Basis 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. 
 
III. - Model AA-5B, Tiger, 4 PCLM, Utility Category, approved November 27, 1974;  Normal Category, approved  
November 27, 1974 
 
Engine One each Lycoming O-360-A4K (Carburetor HA-6 with setting 10-5092 or 10-5219)  
(Type Certificate Number E-286). 
 
Fuel 100/100 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2,700 rpm  (180 hp) 
 
Propeller and Propeller Limits McCauley Model 1A170/FFA7563 with B-4273 spacer (aluminum) or 1A170/KFA7563 
with B-4273 spacer (aluminum), Type Certificate Number P-857.  Static rpm at  
 maximum permissible throttle setting; not over 2325; not under 2175.  Diameter:  not 
over 75 inches; not under 74.5 inches.  No additional tolerance permitted. 
 
Propeller Spinner (Original spinner installation)  Backplate Assembly 5506006-502, Shim 5502035-2, 
Front Bulkhead 5506005-2 or -4 and Spinner Assembly 5506002-1 or -503; or (Globe 
spinner installation)  Bulkhead Assembly Aft 5506008-505, Bulkhead Assembly  
 Fwd 5506010-503, Doubler 5506011-3 and Spinner 5506009-3.

A16EA 
Page 5 
 
 
Airspeed Limits Vne Never exceed 200 mph (174 knots) 
    (CAS) Vno Maximum structural cruising 165 mph (143 knots) 
 Va Maneuvering utility category 130 mph (113 knots) 
 Va Maneuvering normal category 130 mph (113 knots) 
 Vfe Flaps extended 120 mph (104 knots) 
  Canopy partially opened  130 mph (113 knots) 
 
C.G. Range Normal (+89.0) to (+92.50) At 2,400 lbs. 
  (+81.0) to (+92.50) At 1,920 lbs. 
 Utility (+83.17) to (+85.32) at  2,050 lbs. 
  (+81.0) to (+85.32) at 1,520 lbs. 
 Straight line variation between points given.   
 
Empty Weight C. G. Range None 
 
Maximum Weight 2,050 lbs. (Utility Category) 
 2,400 lbs. (Normal Category) 
 
Number of Seats 2  at (+90.6) 
 2 at (+126.0) 
 
Maximum Baggage 120 lbs. at (+148.0) 
 
Maximum Cargo 
  (Rear Seat Folded Down) 340 lbs. at (+116.4) 
 
Fuel Capacity 51 gallons (2 wing tanks)  at  (+94.8) 
 (See NOTE 1 for unusable fuel) 
 
Oil Capacity 8 quarts  at (+32.0) (6 quarts usable) 
 (2 quarts minimum) 
 
Control Surface Movements Elevator 23° ± 1° up 17° ± 2° down 
  (Nominal from neutral) Rudder 25° ± 2° left 25° ± 2° right 
 Ailerons 15° + 2-0° up 7.5° + 2½-0° down 
 Flaps   45° ± 2° down 
 Elevator Trim Tab 14° ± 3° up 30° ± 1° down 
 
Serial Numbers Eligible AA5B-0001 and up  (Normal and Utility Category) 
 
Service Life Limit 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 (Section 5 after 1976), "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 Part Number Service Life  (Hours) 
 Inboard Spar Assembly 5102310-502 12,000 
 Wing Spar Assembly 5201004-501 12,500 
 Wing Outboard Spar Assembly 5201189-501 12,500 
 Shoulder Bolt 901044-2, -3   7,250 
 
Production Basis 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.

A16EA 
Page 6 
 
IV.  Model AG-5B, Tiger, 4 PCLM, Utility Category, approved September 21, 1990; Normal Category, approved  
 September 21, 1990 
 
Engine One each Lycoming O-360-A4K (Carburetor HA-6 with setting 10-5092, 10-5219, or 
10-6019) (Type Certificate Number E-286) 
 
Fuel 100/100 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2,700 rpm  (180 hp) 
 
Propeller and Propeller Limits Sensenich Model 76EM8S10-0-61, 76EM8S10-0-63 and 76EM8S10-0-65.   
 Diameter:  76 inches. (Type Certificate Number P4EA) 
 
Propeller Spinner Bulkhead Assembly Aft 5506008-505, Bulkhead Assembly Fwd 5506010-503, Doubler 
5506011-3 and Spinner 5506009-3. 
 
Airspeed Limits Vne Never exceed 200 mph (174 knots) 
    (CAS) Vno Maximum structural cruising 165 mph (143 knots) 
 Va Maneuvering utility category 130 mph (113 knots) 
 Va Maneuvering normal category 130 mph (113 knots) 
 Vfe Flaps extended 120 mph (104 knots) 
  Canopy partially opened  130 mph (113 knots) 
 
C.G. Range Normal (+89.0) to (+92.50) at 2,400 lbs. 
  (+81.0) to (+92.50) at 1,920 lbs. 
 Utility (+83.17) to (+85.32) at  2,050 lbs. 
  (+81.0) to (+85.32) at 1,520 lbs. 
 Straight line variation between points given. 
 
Empty Weight C. G. Range None 
 
Maximum Weight 2,050 lbs. (Utility Category) 
 2,400 lbs. (Normal Category) 
 
Number of Seats 2  at (+90.6) 
 2 at (+126.0) 
 
Maximum Baggage 120 lbs. at (+148.0) 
 
Maximum Cargo 
  (Rear Seat Folded Down) 340 lbs. at (+116.4) 
 
Fuel Capacity 51 gallons (2 wing tanks)  at  (+94.8) 
 (See NOTE 1 for unusable fuel) 
 
Oil Capacity 8 quarts  at (+32.0) (6 quarts usable) 
 (2 quarts minimum) 
 
Control Surface Movements Elevator 23° ± 1° up 17° ± 2° down 
  (Nominal from neutral) Rudder 25° ± 2° left 25° ± 2° right 
 Ailerons 15° + 2-0° up 7.5° + 2½-0° down 
 Flaps   45° ± 2° down 
 Elevator Trim Tab 14° ± 3° up 30° ± 1° down 
 
Serial Numbers Eligible 10000 and up (Normal and Utility Category) 
 
Service Life Limit 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 (Section 5 after 1976), "Service Life Limited 
 Components."  Service life limits appearing in this manual may not be changed without 
FAA Engineering approval.

A16EA 
Page 7 
 
 Service life limited parts must be retired in accordance with the following schedule: 
 
 Component Part Number Service Life  (Hours) 
 Inboard Spar Assembly 5102310-503 12,000 
 Wing Spar Assembly 5201004-501 12,500 
 Wing Outboard Spar Assembly 5201189-501 12,500 
 Shoulder Bolt 901044-2, -3   7,250 
 
Production Basis None.  Prior to original certification of each aircraft manufactured subsequent to August 
31, 2007, 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. 
 
DATA PERTINENT TO ALL MODELS 
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. 
 
Equipment The basic equipment prescribed in the applicable airworthiness regulations (see 
Certificate Basis) must be installed in the airplane for certification.  In addition, the Pilot 
Operating Handbook/Airplane Flight Manual is required as follows: 
 
• Airplane Flight Manual dated February 26, 1979, is required for the following 
aircraft: 
 
   Model AA-5A:   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. 
 
 
 
• FAA approved Pilot Operating Handbook/Airplane Flight Manual number POH-
AGAC-1 is required for the following model and serial number airplanes: 
 
   Model AG-5B:  S/N 99998, 10000 through 10174. 
 
 
 
• FAA approved Pilot Operating Handbook/Airplane Flight Manual number POH-
AG5B-1 is required for the following model and serial number airplanes: 
 
   Model AG-5B:  S/N 10201 and subsequent except 99998. 
 
 
NOTE 1: A current weight and balance report, including a list of equipment in the certificated empty weight and also 
loading instructions, must be provided for each airplane at the time of original certification.  
 
 A. Applicable to Model AA-5 and Model AA-5A (with Standard Tanks) 
  The certificated weight empty and corresponding center-of-gravity location must include 6 lbs. (1 
gallon) at (+90.9) of unusable fuel.  (Undrainable fuel and oil is negligible.) 
 
 B. Applicable to Model AG-5B, AA-5B and Model AA-5A (with Optional Tanks) 
  The certificated weight empty and corresponding center-of-gravity location must include 9.6 lbs. (1.6 
  gallons) at (+94.8) of unusable fuel.  (Undrainable fuel and oil is negligible.)  The AG-5B also includes 
full oil in the certified weight empty and corresponding center-of-gravity location.

A16EA 
Page 8 
 
NOTE 2: The following placards must be installed in full view of the pilot (values shown below in MPH CAS may be 
provided in KNOTS IAS): 
 
 (a) "THIS AIRPLANE MUST BE OPERATED AS A NORMAL OR UTILITY CATEGORY AIRPLANE 
IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF 
PLACARDS, MARKINGS, AND MANUALS." 
 
 NORMAL CATEGORY 
 MAXIMUM DESIGN WEIGHT 2,200 LBS.  (AA-5 & AA-5A) 
       2,400 LBS.  (AA-5B & AG-5B) 
 
 DESIGN MANEUVERING SPEED, Va 122 MPH CAS (AA-5 & AA-5A) 
       130 MPH CAS (AA-5B & AG-5B) 
 
 FLIGHT LOAD FACTORS: 
  FLAPS UP   +3.8, -1.52 
  FLAPS DOWN  +3.5 
 
 NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED. 
 
 UTILITY CATEGORY 
 MAXIMUM DESIGN WEIGHT 1,850 LBS (AA-5 & AA-5A) 
       2,050 LBS (AA-5B & AG-5B) 
 
 DESIGN MANEUVERING SPEED, Va 122 MPH CAS (AA-5 & AA-5A) 
       130 MPH CAS (AA-5B & AG-5B) 
 
 FLIGHT LOAD FACTORS: 
  FLAPS UP   +4.4, -1.76 
  FLAPS DOWN  +3.5 
 
 REAR SEAT MUST NOT BE OCCUPIED. 
 
 ACROBATIC MANEUVERS ARE LIMITED TO THE FOLLOWING: 
 MANEUVER    ENTRY SPEED (MPH, CAS) 
 
 CHANDELLES   122 (AA-5 & AA-5A) 
       130 (AA-5B & AG-5B) 
 
 LAZY EIGHTS   122 (AA-5 & AA-5A) 
       130 (AA-5B & AG-5B) 
 
 STEEP TURNS   122 (AA-5 & AA-5A) 
       130  (AA-5B & AG-5B) 
 
 STALLS (EXCEPT  SLOW DECELERATION 
   WHIP STALLS) 
 
 SPINS PROHIBITED    
 MAXIMUM ALTITUDE LOSS 350 FEET (AA-5A & AA-5B & AG-5B) 
  IN STALLS   300 FEET (AA-5) 
 
 DEMONSTRATED CROSSWIND 18 MPH (AA-5A & AA-5B & AG-5B) 
  VELOCITY   17 MPH (AA-5) 
 
 THIS AIRPLANE IS NOT APPROVED FOR FLIGHT IN ICING CONDITIONS (AA-5A, AA-5B AND 
 AG-5B).  KNOWN ICING CONDITIONS TO BE AVOIDED (AA-5). 
 
 THIS AIRPLANE IS CERTIFICATED FOR THE FOLLOWING OPERATIONS AS OF DATE  
 OF ORIGINAL AIRWORTHINESS CERTIFICATE. 
 
  IFR, VFR, DAY, NIGHT

A16EA 
Page 9 
 
 
 REFER TO WEIGHT AND BALANCE FOR LOADING INSTRUCTIONS. 
 
 READ FUEL GAUGES IN LEVEL FLIGHT ONLY. 
 
 FOR NORMAL OPERATION, MAINTAIN FUEL BALANCE. 
 
 (b) On left side of cabin: 
   "130 MPH MAXIMUM CANOPY OPEN TO HERE.  NO FLIGHT WITH CANOPY OPEN  
   BEYOND THIS POINT." 
 
 (c) In baggage compartment: 
   "120 POUNDS MAXIMUM BAGGAGE.  FOR ADDITIONAL LOADING INSTRUCTIONS,  
   SEE WEIGHT AND BALANCE DATA.  NO HEAVY OBJECTS ON HAT SHELF." 
 
 (d) On rear seat base  (visible with seat in cargo position): 
   "NO PASSENGERS.  340 POUNDS MAXIMUM CARGO.  DISTRIBUTE EVENLY.  FOR  
   ADDITIONAL LOADING INSTRUCTIONS, SEE WEIGHT AND BALANCE DATA AND  
   OWNER'S MANUAL." 
 
 (e) Under rear seat base  (visible with rear seat back upright): 
   "NO STEP - BEFORE FLIGHT - REAR SEAT MUST BE TURNED DOWN TO COVER THIS 
 AREA." 
 
 (f) Near fuel caps: 
  Model AA-5 and Model AA-5A with Standard Fuel Tanks: 
 
   "FUEL MINIMUM 80/87 OCTANE 19 U.S. GAL. CAP" 
 
  Model AA-5A with Optional Fuel Tanks: 
   "FUEL MINIMUM 80/87 OCTANE 26.3 U.S. GAL. CAP" 
 
  Model AA-5B and Model AG-5B: 
   "FUEL MINIMUM 100/100 OCTANE 26.3 U.S. GAL. CAP" 
 
 (g) Fuel control panel: 
  Model AA-5 and Model AA-5A Standard Fuel Tanks: 
 
LEFT FUEL   RIGHT FUEL 
18.5 GAL.   18.5 GAL. 
 
BOTH OFF 
 
  Model AA-5A Optional Fuel Tanks, Model AA-5B and Model AG-5B Standard Fuel Tanks; 
 
LEFT FUEL   RIGHT FUEL 
25.5 GAL.   25.5 GAL. 
 
BOTH OFF

A16EA 
Page 10 
 
 
 (h) On glove box door: 
   Model AA-5 and Model AA-5A: 
   TIRE PRESSURE  NOSE 21 LBS. 
       MAIN 24 LBS. 
 
   Model AA-5B: 
   TIRE PRESSURE  NOSE 25 LBS. 
       MAIN 34 LBS. 
 
 (i) On instrument panel: 
   "CAUTION:  FLASHING BEACON IN CLOUDS MAY CAUSE VISUAL DISORIENTATION." 
 
   "TURN OFF STROBE IN CLOUD, FOG, OR HAZE.  TAXI WITH STROBE OFF." 
 
  Model AA-5B: 
   "AVOID CONTINUOUS OPERATION BETWEEN 1850 AND 2250 RPM WHILE  
   DESCENDING." 
 
 (j) On left hand side panel: 
   "FOR FLIGHT WITH REAR SEAT OCCUPANTS AND/OR CARGO, CHECK WEIGHT &  
   BALANCE." 
 
   Model AG-5B: 
   TIRE PRESSURE  NOSE 25 LBS. 
       MAIN 34 LBS. 
 
 (k) On baggage door: 
   "TO OPEN DOOR FROM INSIDE, SLIDE HANDLE FORWARD." 
 
 (l) On throttle quadrant: 
   "FRICTION ADJ." 
 
 (m) On eye brow: 
   "NO SMOKING." 
 
NOTE 3: Life limits for each model are found in the section for each individual model. 
 
 
 
...END...
```

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- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 96-09-06](https://openairdocs.org/ad/96-09-06): Air Filter Assemblies · Maule Aerospace Technology 7ACA, 7ECA, 7FC and 180 more. Effective Jun 7, 1996
- [AD 89-18-08](https://openairdocs.org/ad/89-18-08): Fuel Tank/Fuel System · True Flight Holdings AA-5, AA-5A, AA-5B and 1 more. Effective Sep 21, 1989
- [AD 81-24-03](https://openairdocs.org/ad/81-24-03): Engine Power Loss Prevention · True Flight Holdings AA-5, AA-5A and AA-5B. Effective Nov 16, 1981
- [AD 81-15-03](https://openairdocs.org/ad/81-15-03): Engine Inlet Air Filters · Replace existing engine induction air filter (Brackett Aero Filters STC SA693CE or SA71GL). Effective Jul 20, 1981
- [AD 79-22-04](https://openairdocs.org/ad/79-22-04): Aileron System · True Flight Holdings AA-5, AA-5A and AA-5B. Effective Nov 9, 1979
- [AD 79-16-02](https://openairdocs.org/ad/79-16-02): Safety Belt Assemblies · Indiana Mills & Manufacturing Safety Belts, AA-1B, AA-1C and 3 more. Effective Aug 2, 1979
- [AD 77-08-03](https://openairdocs.org/ad/77-08-03): Static System · True Flight Holdings AA-5A and AA-5B. Effective Apr 19, 1977
- [AD 77-07-04](https://openairdocs.org/ad/77-07-04): Carburetor Heat Valve Assembly · True Flight Holdings AA-5 and AA-5A. Effective Apr 11, 1977
- [AD 76-22-09](https://openairdocs.org/ad/76-22-09): Oil Coolers · True Flight Holdings AA-5A and AA-5B. Effective Nov 10, 1976
- [AD 76-17-03](https://openairdocs.org/ad/76-17-03): Delaminations in Bonded Skin · True Flight Holdings AA-1, AA-1A, AA-1B and 3 more. Effective Aug 30, 1976
- [AD 76-01-02](https://openairdocs.org/ad/76-01-02): Engine Cowl · True Flight Holdings AA-5, AA-5A and AA-5B. Effective Feb 25, 1976
- [AD 76-04-05](https://openairdocs.org/ad/76-04-05): Carburetor Mixture Control Wire · True Flight Holdings AA-5B. Effective Feb 25, 1976
- [AD 72-06-02](https://openairdocs.org/ad/72-06-02): Rudder Aileron and Elevator Control Cables · True Flight Holdings AA-1, AA-1A, AA-1B and 1 more. Effective Aug 29, 1974
- [AD 75-07-04](https://openairdocs.org/ad/75-07-04): Rudder Control Bar Assemblies · True Flight Holdings AA-1, AA-1A, AA-1B and 2 more
- [AD 95-19-15](https://openairdocs.org/ad/95-19-15) (historical): Wing Attach Shoulder Bolts · American General Aircraft Holding AA-5, AA-5A, AA-5B and 1 more. Effective Nov 17, 1995

## Registered aircraft by registry model (OpenAirDocs)

- [Grumman American Avn. AA-5B](https://openairdocs.org/model/grumman-american-avn-aa-5b): 643 aircraft (registry code 3960105)
- [Grumman American Avn. AA-5A](https://openairdocs.org/model/grumman-american-avn-aa-5a): 386 aircraft (registry code 3960106)
- [Grumman American Avn. AA-5](https://openairdocs.org/model/grumman-american-avn-aa-5): 257 aircraft (registry code 3960104)
- [Gulfstream American AA-5B](https://openairdocs.org/model/gulfstream-american-aa-5b): 216 aircraft (registry code 3970106)
- [American AA-5](https://openairdocs.org/model/american-aa-5): 127 aircraft (registry codes 0631410, 0630711)
- [American General Acft AG5B](https://openairdocs.org/model/american-general-acft-ag5b): 114 aircraft (registry code 3990100)
- [Gulfstream American AA-5A](https://openairdocs.org/model/gulfstream-american-aa-5a): 99 aircraft (registry code 3970104)
- [Tiger AG-5B](https://openairdocs.org/model/tiger-ag-5b): 46 aircraft (registry code 3990101)
- [Gulfstream Aerospace AG-5B](https://openairdocs.org/model/gulfstream-aerospace-ag-5b): 1 aircraft (registry code 3980275)
- [Grumman AG5B](https://openairdocs.org/model/grumman-ag5b): 0 aircraft (registry code 3950415)

## STCs approved under this data sheet (247, first 50)

- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation
- [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies
- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc.
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc.
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc.
- [STC SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. Garmin International Inc.
- [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA863SO](https://openairdocs.org/stc/SA863SO): Installation of portable hand control. Union Aviation LLC
- [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc.
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA04400NY](https://openairdocs.org/stc/SA04400NY): Installation of the Integrated Back-up Battery System (IBBS). TCW Technologies LLC
- [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc
- [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine
- [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation
- [STC SA04586CH](https://openairdocs.org/stc/SA04586CH): Installation of Electroair Back Up Battery Panel System Control. Electroair Aquisition Corp.
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA02057AT](https://openairdocs.org/stc/SA02057AT): Installation of a composite nose bowl.. Whelen Aerospace Technologies
- [STC SA1169NW](https://openairdocs.org/stc/SA1169NW): Installation of a Lycoming O-360-A4K engine and a Sensenich76EM8S10-0-63 propeller.. Fletchair Inc.
- [STC SA1186NW](https://openairdocs.org/stc/SA1186NW): Installation of a Lycoming O-360-A4K engine, a McCauley 1A170FFA/7563 or a Sensenich76EM8S10-0-60 thru -65 propeller and associated systems.. Fletchair Inc.
- [STC SA1299NW](https://openairdocs.org/stc/SA1299NW): Installation of a McCauley propeller on Lycoming O-320-E2G engine.. Fletchair Inc.
- [STC SA1767NM](https://openairdocs.org/stc/SA1767NM): Alteration of the oil cooler and air induction system.. Fletchair Inc.
- [STC SA2125NM](https://openairdocs.org/stc/SA2125NM): Installation of Lycoming O-360-A4M engine and Sensenich76EM8S10-0-60 propeller.. Fletchair Inc.
- [STC SA2620NM](https://openairdocs.org/stc/SA2620NM): Modify engine baggles and relocate oil cooler to above and behind the left hand rear cylinder on Lycoming O-360-A4K engine with Sensenich76EM8S10-0-63 propeller.. Fletchair Inc.
- [STC SA4165NM](https://openairdocs.org/stc/SA4165NM): Installation of a Lycoming O-540-E4A5 engine and a Hartzell Model HC-C2YK-8477-8R propeller. Fletchair Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King)
- [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc.
- [STC SA02251LA](https://openairdocs.org/stc/SA02251LA): Installation of fiberglass cowling and improved engine baffles.. Kevin Lancaster
- [STC SA02533LA](https://openairdocs.org/stc/SA02533LA): Installation of improved carburetor air inlet and filter housing. Kevin Lancaster
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation

All 247: https://openairdocs.org/tcds/A16EA/stcs.md

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