TCDS T00003LA

P a g e 1234 R e v ---- DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION T00003LA Reid Dennis HU-16RD December 3, 1998 TYPE CERTIFICATE DATA SHEET NO. T00003LA This data sheet, which is a part of the Type Certificate No. T00003LA, 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 Reid Dennis 300 Sand Hill Road Building 2, Suite 290 Menlo Park, California 94025 I - Model HU-16RD (Albatross) (Restricted Category) approved Engine (2) Wright 982C9HE3 (Military Designation R-1820-82C) See TCDS E-259-6 Fuel Minimum 100 octane low lead (100LL) Fuel Capacity Usable Total Capacity Arm Right & left main tanks 338 US gal. (each) 340 US gal. (each) +297.3 Right & left aux tanks 320 US gal. (each) 323 US gal. (each) +297.3 Right & left float tanks 206 US gal. (each) 209 US gal. (each) +307.5 Engine Oil MIL-L-6082 Grade 1120 or Grade 1100 MIL-L-22851 (WEP) Grade 1120 or Grade 1100 Oil Capacity 29 US gal. (each tank) usable and total, (+262.0) Engine Limits Phase BHP RPM MP Altitude Takeoff (5 min) 1475 2800 54.5 SL Takeoff (5 min) 1475 2800 54.0 1250 ft. Max continuous 1275 2500 46.5 SL Max continuous 1275 2500 45.5 2550 ft. Operations between 2100 and 2200 RPM; 2550 and 2650 is restricted to passing through only. Minimum allowable oil pressure at idle speed is 15 PSI. Minimum allowable oil pressure above 1450 RPM is 65 PSI. At or below 1450 lower pressures may be observed. These values are acceptable providing the oil pressure check is within limits. T00003LA Page 2 of 4 Propeller & Propeller Limits (2) Hamilton Standard 43D51-667 See TCDS P-851-16 (3) 7113( )-5 blades 11 ft. 2 in. diameter Pitch setting at the 54 inch blade station Full reverse -18 ° Low pitch stop +13 ° High pitch stop +84 ° Maximum allowable engine RPM in reverse pitch is 2500 RPM Airspeed Limits V NE 260 KIAS VNO 206 KIAS VA 130 KIAS VFE 15° 175 KIAS 30° 135 KIAS 40° 115 KIAS VLO 130 KIAS VLE 130 KIAS VLLE 120 KIAS VRB 150 KIAS VMC 85 KIAS C. G. Range 294” to 304” Datum 149” forward of the jig point in the nose wheel well. Leveling Means Leveled laterally by leveling lugs located in the nose wheel well and longitudinally by a plumb bob drop from the small hole located in the shelf of the left wheel well. Maximum Weight Phase Landplane Seaplane Ramp/water taxi 33,650 lbs. 29,650 lbs. Takeoff 33,500 lbs. 29,500 lbs. Landing 29,500 lbs. 29,500 lbs Minimum Crew 2 (pilot & copilot) Maximum number of crew shall not exceed 12 including pilot and copilot. Maximum number of seats is 13 including pilot and copilot. Capacity Arm Baggage Compartment 1 200 lbs. +248.0 2 150 lbs. +300.0 3 100 lbs. +417.0 4 50 lbs. +456.0 Page 3 of 4 T00003LA Control Surface Movement Ailerons Up 17° ±1° Down 17° ±1° Elevator Up 30° ±1° Down 20° ±1° Rudder Right 20° ±1° Left 15° ±1° Aileron Trim Tab Up 18° ±1° Down 12° ±1° Elevator Trim Tab Up 5° ±1° Down 12° ±1° Rudder Trim Tab Right 16° ±1° Left 26° ±1° Serial Numbers Eligible 137932 Certification Basis Federal Aviation Regulations (FAR) 21.25(a)(2) and (b)(3) effective February 1, 1965, Amendment 21-1 through 21-75. For the special purpose of aerial surveying. For modifications made to the airplane, CAR 4b and/or FAR Part 25 was required only for the following specific paragraphs: CAR 4b.200, 4b201(c), 4b.221, 4b.270(a)(2), 4b.301, 4b.302, 4b.303, 4b.304, 4b.306, 4b.307(c) for Structures, CAR 4b.300, 4b.301, 4b.325, 4b.326, 4b.329, 4b.334(c), 4b.335 through .337, 4b.350, 4b.356, 4b358, 4b.371, 4b.381 thro ugh .385, 4b.650, 4b.652 through 4b.655, 4b.601, 4b.603(b), 4b.604(d)(h), 4b.605(f), 4b.606, 4b.612(f), 4b.624, 4b.625, 4b.630(i), 4b.631(d), 4b.632, 4b.633, 4b.634, 4b.636, 4b.637, FAR 25.1316(b)(c) for Systems & Equipment; 4b.400 through 4b.407 for engines and propellers; and 4b.410 through 4b.437 for Fuel Systems; FAR 25.143, .145, .147, .149, .171, .175, .177, .181, .201, .203 for Flight Test; 14CFR Part 36, effective December 1, 1969, through amendment 36-1 for noise. Date of application for Type Certificate: June 30, 1994. 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 1, 1998. A finding under the applicable provisions of the Noise Control Act of 1972 has been accomplished and approved on March 21, 1998, for the modified Grumman HU-16C (UF-1) aircraft (Restricted Category - Military Surplus). Production Basis None. Prior to original certification, an FAA representative must perform an inspection for workmanship, materials and conformity with the approved technical data. Equipment The basic required equipment as prescribed in the applicable Airworthiness Regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the FAA approved Airplane Flight Manual dated November 25, 1998, or later FAA approved revision, is required. Tires Mains Goodyear P/N 402F03B1 B. F. Goodrich P/N 033-753 Nose Goodyear P/N 266F08-4 B. F. Goodrich P/N 038-657-2 T00003LA Page 4 of 4 NOTES Note 1 Current weight and balance report including a list of equipment included in the certificated empty weight, and loading instructions, when necessary, must be in the aircraft at the time of the original certification. Note 2 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 the operating limitations stated in the FAA approved Airplane Flight Manual. 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 of the Convention of International Civil Aviation.” Note 3 This aircraft must be serviced and maintained in accordance with TO 1U- 16(H)A/B-2 or NAVWEPS 01-85AB-2 and the approved inspection program. Note 4. This approval applies to airplane S/N 137932 modified in accordance with Drawing RD100000, Rev. Z, or later FAA approved revisions. Note 5 The modification data plate in restricted category must be installed next to the manufacturer’s data plate in the cockpit. Note 6 Flight into known icing conditions is prohibited. Note 7 This aircraft is not equipped or approved for operation with the JATO system. Note 8 This aircraft is not equipped or approved for operation with an APU. Note 9 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 of 21.25 (b)(3) Aerial Surveying (ref. FAR 91.313). Seating configuration is defined by drawing number RD252301, revision 6, dated December 2, 1998, or later FAA approved revisions. - END -