TCDS A23NM

P a g e N o . 12345678 R e v . N o . 43344344 FEDERAL AVIATION ADMINISTRATION A23NM Revision 4 BUEHN HU-16C (UF-1) TU-16C (UF-1T) SA-16A (UF-1) September 10, 1998 TYPE CERTIFICATE DATA SHEET NO. A23NM This data sheet, which is a part of Type Certificate No. A23NM, 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 Dennis G. Buehn 2600 Graves #33 Carson City, Nevada 89706 I - Model HU-16C (UF-1) (Navy), (Restricted Category), Approved August 17, 1988 Model TU-16C (UF-1T) (Navy Trainer) (Restricted Category), Approved December 23, 1988 (See Note 12) Engine (2) Wright R-1820-76A, B, C or D, Single Stage, Two Speed Engines, Geared 3 to 2 Reduction Gearing Fuel 100/130 or 100 LL Grade Aviation Fuel Engine Limits (Per AN 01-85-AB-1) Power Setting RPM MP In. Hg. Mixture BHP Take-off (30 min.) 2700 51.5 Rich 1425 Military 2700 50.5 Normal 1425 Normal Rated (Max. Cont.) 2500 46.5 Normal 1275 High Cruise 2250 37.0 Normal 950 Propellers Hamilton Standard Matched Hubs and Propellers Hub Designation Applicable Propellers* 43D50-601 6601A-7 thru -9, 6621A-7, 6621B-7, 6999-7 thru -9, 7005-7, 7007B, 7007B-7 43D50-603 6601A-7 thru -9, 6601B-7, 6621A-7, 6999-7 thru -9, 7005-7, 7007B, 7007B-7 43D50-605 6621B-7 43D50-609 7001B-7, 7003B-7, 7007B-7 43D50-613 7001B-7, 7003B-7, 7007B-7 43D50-615 7007C-7 43D50-637 6601A-7 thru -9, 6621A-7, 6999-7 thru -9, 7005-7, 7007B, 7007B-7, 7007F-7 43D50-639 7007E-7, 7007F-7 43D50-641 7001C-7, 7003C-7 *Propellers must be used in matched sets on each hub Diameter 11 feet Pitch settings: Low (fine) 16°, High (feathered) 89°, Reverse -12° A23NM Page 2 of 8 Airspeed Limits Maximum permissible indicated airspeeds are as follows per AN 01-85AB-1 Flight Handbook: Smooth Air 260 Knots Flaps 15° 175 Knots Flaps 30° 135 Knots Flaps 45° 115 Knots Gear Down 130 Knots Landing Lights Down 120 Knots Full Aileron Deflection 175 Knots Severe Turbulence 110-130 Knots C. G. Range +20.5 MAC to +28.0 MAC Datum See T. O. 1-1B-40 (AN 01-1B-40) Chart E with Dennis Buehn Cargo Tie-Down Appendix. Field Take-off Weight 33,500 lbs. Field Landing Weight 29,500 lbs. Water Take-off & Landing 29,500 lbs. Leveling Means See AN-01-1B-40, Chart E Minimum Crew Two (Pilot and Co-Pilot) Cargo Capacity See T. O. 1-1B-40, Chart E Fuel Capacity 675 gals. (2) Main Tanks 414.5 gals. (2) Float Tanks 150 or 300 gals. (2 ea.) Auxiliary Tanks Oil Capacity 58 gals. (2) Nacelle at 29 gals. each Settings & Ranges of Movement of Control Surfaces and Flaps (Per 01-85AB-2, Section 1) Movements Tolerances Degrees Inches Degrees Inches Ailerons Up (from Neutral) 17 6½ ±1 ±3/16 Down (from Neutral) 17 6½ ±1 ±3/16 Elevators Up (from streamline with stabilizer) 30 15 ±1 ±3/16 Down (from streamline with stabilizer) 20 10-1/16 ±1 ±3/16 Rudder Right (from streamline with fin) 20 ±1 ±3/16 Left (from streamline with fin) 15 ±1 ±3/16 Flaps Up (measured at inboard end) 0 15 0 12-1/32 - ±3 ±3/32 ±2-13/32 Full 30 24-2/32 ±3 ±2-13/32 Down 40 32-1/32 ±3 ±2-13/32 A23NM Page 3 of 8 Settings & Ranges of Movement of Control Surfaces and Flaps (Continued) (Per 01-85AB-2, Section 1) Movements Tolerances Degrees Inches Degrees Inches Trim Tabs Elevator Up (from elevator trailing edge) Down (from elevator trailing edge) 5 12 23/32 1-21/32 ±1 ±1 ±1/8 ±1/8 Rudder Right (from rudder trailing edge) Left (from rudder trailing edge) 17 25 3-5/16 4-27/32 ±1 ±1 ±3/16 ±3/16 Aileron Up (from aileron trailing edge) Down (from aileron trailing edge) 18 12 1-5/8 1-1/16 ±1 ±1 ±3/32 ±3/32 Serial Nos. Eligible Model HU-16C (UF-1) (Navy) Factory Number Bureau Number 10 124374 16 124376 19 124377 22 124378 25 124379 90 149836 (Ex 51-17) 233 131890 236 131891 239 131892 242 131893 245 131894 249 131895 252 131896 254 131897 257 131898 261 131899 264 131900 269 131902 273 131903 278 131905 281 131906 284 131907 290 131909 293 131910 296 131911 311 131916 333 131904 338 131908 367 1290* (142360) 368 1291* (142361) 369 1292* (142362) 373 137900 A23NM Page 4 of 8 Serial Nos. Eligible (cont’d) Model HU-16C (UF-1) (Navy) Factory Number Bureau Number 375 137902 378 137905 381 137908 382 137909 385 137912 388 137905 389 137916 396 137923 397 137924 398 137925 399 137926 400 137927 401 137928 402 137929 403 137930 405 137932 406 137933 409 141262 412 141265 414 141267 418 141271 420 141273 423 141276 424 141277 *Previously UF-1CG (Coast Guard) Model TU-16C (UF-1T) 305 131914 308 131915 311 131916 314 131917 320 131918 Certification Basis Type Certificate A23NM, issued August 17, 1988, for the special purpose of carriage of cargo. Reference to Advisory Circular 21.17, dated March 14, 1982, specifies that carriage of cargo is considered a special purpose under FAR 21.25(b)(7). Date of application December 8, 1986. The modifications incorporated are considered appropriate to the special purpose operation. The criteria established in Civil Regulations Part 4b appropriate to the special purpose operation has been used to evaluate these particular changes and demonstrate that the original level of airworthiness established by the military requirements has not been reduced. A Finding of No Significant Impact (FONSI) for the modified Grumman (Navy) Model HU-16C (UF-1) aircraft has been accomplished and approved on March 21, 1988. A finding under the applicable provisions of the Noise Control Act of 1972 has also been accomplished and approved on March 21, 1988, for the modified Grumman HU-16C (UF-1) aircraft (Restricted Category- Military Surplus). Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed. In addition, NAVWEPS Flight Manual (NAVY), 01-85AB-1, revised April 8, 1965, with Dennis G. Buehn FAA Approved AFM Supplement No. 1 to NAVWEPS 01-85AB-1 with Dennis Buehn cargo tie down appendix is required. A23NM Page 5 of 8 Date of Application December 8, 1986 Production Basis None. Prior to original certification, an FAA representative must perform an inspection for workmanship, material, and conformity with the approved technical data. Applicable Technical Orders affecting airworthiness must be accomplished. II Model SA-16A (UF-1) (USAF) (Restricted Category), Approved September 10, 1998 (See Note 13) Engine (2) Wright R-1820-76A, B, C or D, Single Stage, Two Speed Engines, Geared 3 to 2 Reduction Gearing Fuel 100/130 or 100 LL Grade Aviation Fuel Engine Limits (Per AN 01-85-AB-1) Power Setting RPM MP In. Hg. Mixture BHP Take-off (30 min.) 2700 51.5 Rich 1425 Military 2700 50.5 Normal 1425 Normal Rated (Max. Cont.) 2500 46.5 Normal 1275 High Cruise 2250 37.0 Normal 950 Propellers Hamilton Standard Matched Hubs and Propellers Hub Designation Applicable Propellers* 43D50-601 6601A-7 thru -9, 6621A-7, 6621B-7, 6999-7 thru -9, 7005-7, 7007B, 7007B-7 43D50-603 6601A-7 thru -9, 6601B-7, 6621A-7, 6999-7 thru -9, 7005-7, 7007B, 7007B-7 43D50-605 6621B-7 43D50-609 7001B-7, 7003B-7, 7007B-7 43D50-613 7001B-7, 7003B-7, 7007B-7 43D50-615 7007C-7 43D50-637 6601A-7 thru -9, 6621A-7, 6999-7 thru -9, 7005-7, 7007B, 7007B-7, 7007F-7 43D50-639 7007E-7, 7007F-7 43D50-641 7001C-7, 7003C-7 *Propellers must be used in matched sets on each hub Diameter 11 feet Pitch settings: Low (fine) 16°, High (feathered) 89°, Reverse -12° Airspeed Limits Maximum permissible indicated airspeeds are as follows per AN 01-85AB-1 Flight Handbook: Smooth Air 260 Knots Flaps 15° 175 Knots Flaps 30° 135 Knots Flaps 45° 115 Knots Gear Down 130 Knots Landing Lights Down 120 Knots Full Aileron Deflection 175 Knots Severe Turbulence 110-130 Knots C. G. Range +20.5 MAC to +28.0 MAC Datum See T. O. 1U-16 (H)A-5 (USAF) with Dennis Buehn Cargo Tie-Down Appendix. A23NM Page 6 of 8 Field Take-off Weight 33,500 lbs. Field Landing Weight 29,500 lbs. Water Take-off & Landing 29,500 lbs. Leveling Means See AN-01-1B-40, Chart E Minimum Crew Two (Pilot and Co-Pilot) Cargo Capacity See T. O. 1-1B-40, Chart E Fuel Capacity 675 gals. (2) Main Tanks 414.5 gals. (2) Float Tanks 150 or 300 gals. (2 ea.) Auxiliary Tanks Oil Capacity 58 gals. (2) Nacelle at 29 gals. each Settings & Ranges of Movement of Control Surfaces and Flaps (Per 01-85AB-2, Section 1) Movements Tolerances Degrees Inches Degrees Inches Ailerons Up (from Neutral) 17 6½ ±1 ±3/16 Down (from Neutral) 17 6½ ±1 ±3/16 Elevators Up (from streamline with stabilizer) 30 15 ±1 ±3/16 Down (from streamline with stabilizer) 20 10-1/16 ±1 ±3/16 Rudder Right (from streamline with fin) 20 ±1 ±3/16 Left (from streamline with fin) 15 ±1 ±3/16 Flaps Up (measured at inboard end) 0 15 0 12-1/32 - ±3 ±3/32 ±2-13/32 Full 30 24-2/32 ±3 ±2-13/32 Down 40 32-1/32 ±3 ±2-13/32 Trim Tabs Elevator Up (from elevator trailing edge) Down (from elevator trailing edge) 5 12 23/32 1-21/32 ±1 ±1 ±1/8 ±1/8 Rudder Right (from rudder trailing edge) Left (from rudder trailing edge) 17 25 3-5/16 4-27/32 ±1 ±1 ±3/16 ±3/16 Aileron Up (from aileron trailing edge) Down (from aileron trailing edge) 18 12 1-5/8 1-1/16 ±1 ±1 ±3/32 ±3/32 Serial Nos. Eligible Model SA-16A (UF-1) (USAF) Factory Number Bureau Number 32 49-074 A23NM Page 7 of 8 Certification Basis Type Certificate A23NM, issued August 17, 1988, for the special purpose of carriage of cargo. Reference to Advisory Circular 21.17, dated March 14, 1982, specifies that carriage of cargo is considered a special purpose under FAR 21.25(b)(7). Date of application December 8, 1986. The modifications incorporated are considered appropriate to the special purpose operation. The criteria established in Civil Regulations Part 4b appropriate to the special purpose operation has been used to evaluate these particular changes and demonstrate that the original level of airworthiness established by the military requirements has not been reduced. A Finding of No Significant Impact (FONSI) for the modified Grumman (Navy) Model HU-16C (UF-1) aircraft has been accomplished and approved on March 21, 1988. A finding under the applicable provisions of the Noise Control Act of 1972 has also been accomplished and approved on March 21, 1988, for the modified Grumman HU-16C (UF-1) aircraft (Restricted Category- Military Surplus). These findings also apply to the Grumman (Navy Trainer) Model TU-16C (UF-1T) and to the Grumman (Air Force) Model SA-16A (UF-1) aircraft. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed. In addition, NAVWEPS Flight Manual (USAF) T.O. 1U-16(H)A-1, revised April 8, 1965, with Dennis G. Buehn FAA Approved AFM Supplement No. 1 to NAVWEPS 1U-16(H)A-1 with Dennis Buehn cargo tie down appendix is required. Date of Application May 27, 1996 Production Basis None. Prior to original certification, an FAA representative must perform an inspection for workmanship, material, and conformity with the approved technical data. Applicable Technical Orders affecting airworthiness must be accomplished. NOTES Note 1 Current weight and balance information, including a list of equipment in certified empty weight and loading instructions, must be in the airplane at time of original airworthiness certification and all times thereafter. Each compartment, respectively, must have a placard showing the maximum loading weight for that compartment. Cargo must be loaded on the airplane in accordance with T.O. 01-18-40, and must be secured using TSO straps or nets anchored to wedjit tie-down fasteners installed in the airplane. (See AFM Supplement No. 1 to NAVWEPS Flight Manual 01-85AB-1 with Dennis Buehn cargo tie down appendix for compartment loading chart and anchoring instructions.) Note 2 The initial, minimum scheduled maintenance program requirements for the UH-16C and the TU-16C are contained in document DGB 16-2. This document also applies to the SA-16A. A. The airplane must satisfactorily pass an inspection for conformity with 01-85AB-2 (for Models HU-16C and TU-16C) or T.O. 1U-16(H)A-2-1 (for Model SA-16A) for possible hidden damage and for workmanship and materials used in making any repairs and/or alterations. B. The maintenance, overhaul and modification records must be reviewed for changes made by the military services that may have an effect on the airworthiness of the airplane. Modifications and changes of equipment which affect the safety or performance of the airplane must be approved by the Federal Aviation Administration. C. Conduct an inspection of the engine support structures to verify their structural integrity. D. This aircraft is not equipped or approved for operation with JATO system. A23NM Page 8 of 8 Note 2 (cont’d) E. This aircraft is not equipped or approved for operation with APU. F. Engine supercharger high speed ratio (high blower) must be permanently deactivated for all operations. G. The modification data plate in restricted category must be installed next to manufacturer’s data plate in the cockpit. H. Aircraft must be flight tested and FAA Form 8130-9 completed. Note 3 Reserved. Note 4 Carriage of hazar dous materials is prohibited unless compliance is shown with applicable regulations in the Code of Federal Regulations, Title 49, Part 175. Note 5 The following note must be placed under "exceptions" on all Export Certificates of Airworthiness for this airplane. "This airplane is type certificated in the restricted category and may not meet the applicable airworthiness code as provided by Annex 8 to the Convention of International Civil Aviation." Note 6 Flight into known ic ing conditions is prohibited. Note 7 Approved cargo nets/straps to be FAA TSO'd equipment. Note 8 Two (2) oxygen masks providing 100% breathing capacity for both pilots, and two (2) smoke masks, are required for flight in the aircraft at all times. Note 9 Two (2) fire extinguishers must be installe d - one in the cockpit and one in the cabin are required. Note 10 This approval applies to this airplane modified in accordance with Drawing No. DGB16-1 dated January 12, 1988, or later FAA approved revision. Note 11 The following placard must be installed in clear view of the pilot: RESTRICTED CATEGORY This airplane must be operated as a restricted category airplane and in accordance with operating limitations stated in NAVWEPS 01-85AB-1 (Navy models) or T.O. 1U- 16(H)A-1 (USAF models), Dennis G. Buehn FAA Approved AFM Supplement No. 1, and in accordance with all placards and manuals. No persons may be carried on a restricted category civil aircraft unless they are necessary for the accomplishment of the work activity directly associated with that special purpose. Ref. 91.313(d) (formerly 91.39(c)(4)). Note 12 Navy Trainer Model UF-1T airplanes are identical to the standard Navy UF-1 airplanes except that they are equipped with additional navigation instruments and extra cabin equipment. Note 13 USAF Model SA-16A airplanes are esse ntially identical to the standard Navy UF-1 airplanes. - END -