What it approves
Installation of Lycoming IO-540 series engines.
What the certificate saysOCR
This is OCR from the scanned FAA certificate. OCR can misread letters and numbers.
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA1368WE This certificate issued to: RILEY TURBOSTREAM CORPORATION Part * of the Regulations: * See page 8 of this STC for certification basis.
Original Product -Typelertificate Number: 816 Make: de Havilland Model: D.H. 114 Heron Series 2A, 2DA, 2X Description of Type Design Change: Installation of Lycoming 10-540 series engines.
See pages 3 through 8 of this STC for required descriptive data.
Limitations and Conditions: The limitatione and conditions of Aircraft Specification No. A-816 apply except as outlined in pages 3 through 10 of this STC.
Watson Chief, Engineering and Manufacturing Branch (Title)
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA136851 February 23, 1977 Limitations and Conditions:
I - Model D.H. 114 Heron Series 2X as modified by this STC (Basic configuration and configuration B). Approved March 3, 1967 Configuration B same as Basic Configuration except for simplified cockpit controls.
Engines Four Lycoming I0-540-GIA5 or 10-540-KIC5 modified in accordance with STC SEWE to incorporate turbosuperchargers. See NOTE 4.
Fuel 100/130 Minimam Grade Aviation Gasoline Engine Limits 29.5 in.hg. 2575 rpm (290 HP) for all operations from sea level to maximum operating altitude of 17,000 feet.
Propellers Four Hartzell HC-A3VK-2/V8433-7 constant speed Propeller Limits Pitch settings at 30 in. station Low 14°, Feather 79° Diameter 76.625 inches to 77.625 inches.
Airspeed Limits Normal Operating Limit Never Exceed Flaps extended 0-20° 20° to fully extended Landing Gear Extended 174 knots (200 MPH) I.A.S.
200 knots (230 MPH) I.A.S.
135 kots (155 MPH) I.A.S.
100 knots (115 MPH) I.A.S.
135 knots (155 MPH) I.A.S.
C.G.range (with (-1.46) to (+4.6) at 12,499 lbs.
landing gear (-6.35) to (+4.6) at 8,900 lbs. or less extended) Distances show are plus (+) behind and minus (-) ahead of the datum.
Straight line variation betveen points given.
Landing gear retraction moment +3180 in.1b.
Maximum weight Takeoff 12,499 Ibs. Landing 11,900 1bs.
See NOTE 2 for 12,499 1bs. landing weight) Maximum operating 17,000 ft. M.S.L.
altitude
FAA FORM 8110-2-1 (10-69) PAGE 30F 10PAGES FAA AC 72-4435
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA1368WE February 23, 1977 Minimum crew TWO Fuel capacity 378 U. S. gallons (in wings) (usable) Two tanks 67 U. S. gallons each (+5.5) Two tanks 122 U.S. gallons each (+21.6) 01l capacity 13 U. S. quarts per engine (-58.5) Serial Nos. All Series 2X airplanes that are eligible for U.S.
eligible Airworthiness Certification under Type Certificate No. 816 and have been modified in accordance with FAA Sealed Technical Service Summary Drawing No. 828.
Drawing 828 Revision "p" or subsequent FAA Sealed revision is required for Basic Configuration aircraft, and Draving 828 Revision 'p" or subsequent FAA Sealed revision is required for Configuration B aircraft. See NOTE 5.
II - Model D.ll. 114 Heron Series 2X as modified by this STC (Configuration A).
Approved November 21, 1967 Same as Basic Configuration except for installation of non-supercharged engines.
Engines Four Lyconing I0-540-GIAS or 10-540K1C5 - See NOTE 4.
Fuel 100/130 Minimum Grade Aviation Gasoline Engine limits 2575 pm, full throttle (290 HP) for all operations Propellers Four Hartzell HC-A3VK-2/V8433-7 constant speed Propeller limite Pitch settings at 30 in. station Low 14°, Feather 79° Diameter 76.625 inches to 77.625 inches Airspeed limits Normal operating limit Never Exceed Flaps extended 0-20° 20° to fully extended Landing gear extended 174 Imots (200 MPH) I.A.S.
200 knots (230 MPH) I.A.S.
135 knots (155 MPH) I.A.S.
100 knots (115 MPH) I.A.S.
135 knots (155 MPH) I.A.S.
FAA FORM 8110-2-1 (10-69) PAGE# OF 10 PAGES
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA1368WE February 23, 1977 C.G. range (with (-1.46) to (+4.6) at 12,499 lbs.
Landing gear (+6.25) to (+4.6) at 8,900 lbs. or less extended) Distances shown are plus (+) behind and minus (-) ahead of the datum.
Straight line variation between points given.
Landing gear retraction moment +3180 in.lbs.
Maximum weight Takeoff 12,499 1bs., landing 11,900 1bs.
(See NOTE 2 for 12,499 1bs. landing weight) Maximum operating 17,000 ft. M.S.L.
altitude Minimum crew Two Fuel capacity 378 U.S. gallons (in wings) (usable) Two tanks 67 U.S. gallons each (+5.5) Two tanks 122 U.S. gallons each (+21.6) 01l Capacity 13 U.S. quarts per engine (-58.5) Serial Nos. All Series 2X airplanes that are eligible for U.S.
eligible Alavorthinese Certification under Type Certificate No. 816 and have been modified in accordance with FAA Sealed Aircraft Technical Service Summary Draving 828 Revision "H" or subsequent FAA Sealed revision. See NOTE 5.
III - Model D.H. 114 Heron Series 2A or 2DA as modified by this STC (Configuration D). Approved April 9, 1968 The modifications are identical for Basic Configuration and Configuration D.
Engines Four Lycoming I0-540-G1A5 or 10-540-KIC5 modified in accordance with STC SE6WE to incorporate turbosuperchargers. See NOTE 4.
Fue 1 100/130 Minimum Grade Aviation Gasoline Engine limita 29.5 in.hg, 2575 rpm (290 HP) for all operations from sea level to maximum operating altitude of 17,000 feet.
FAA FORM 8110-2-1 (10-69) PAGE 5°F 10 PAGES FAA AC 72-4435
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA1368WE February 23, 1977 Propellers Four Hartzel1 HC-A3VK-2/V8433-7 constant speed Propeller limits Pitch settings at 30 in. station Low 14° Feather 79° Diameter 76.625 inches to 77.625 inches.
Airspeed Limits Normal Operating limit Never Exceed Flaps extended 0-20° 20° to fully extended Landing gear extended 174 knots (200 MPH) I.A.S.
200 knots (230 MPH) I.A.S.
135 knots (155 MPH) I.A.S.
100 knots (115 MPH) I.A.S.
135 knots (155 MPH) I.A.S.
C.G. range (with (-1.46) to (14.6) at 12,499 Ibs.
landing gear (-6.35) to (14.6) at 8,900 lbs. or less extended) Distances shown are plus (+) behind and minus (-) ahead of the datum.
Straight line variation betveen points given.
Landing gear retraction moment +3180 in.lb.
See NOTE 3 for C.G. range at higher maximum weights.
Maximum weight Takeoff 12,499 lbs., landing 12,499 Ibs.
See NOTE 3 for increased weights Maximum operating 17,000 ft. M.S.L..
altitude Miniman crew 1WO Fuel capacity 494 U.S. gallons (in Wings) (usable) Two tanks 67 U.S. gallons each (-5.5) Two tanks 122 U.S. gallons each (+21.6) Two pairs of tanks 58 U.S. gallons per pair (-4.56) Oil capacity 13 U.S. quarts per engine (-58.5) Serial Nos. All Series 2A and 2DA airplanes that are eligible for eligible U.S. Airworthiness Certification under Type Certificate No. 816 and have been modified in accordance with FAA Sealed Aircraft Technical Service Summary Draving 828 Revision "D" or subsequent FAA Sealed Revision.
See NOTE 5.
FAA FORM 8110-2-1 (10-69) PAGE 6 OF 10PAGES
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number February 23, 1977 94368WB IV - Model D.H. 114 Heron Series 2A or 2DA as modified by this STC (Configuration C), Approved July 26, 1968 The modifications are identical for Configuration A and C except for the addition of an elevator down spring in the Configuration C.
Engines Four Lycoming I0-540-GIAS or 10-540-KICS See NOTE 4.
Fuel 100/130 Minimum Grade Aviation Gasoline Engine Limits 2575 rpm, full throttle (290 HP) for all operations Propellera Four Hartzall HC-A3VK-2/V8433-7 constant speed Propeller Limits Pitch settings at 30 in. station. Low 140 Feather 79° Diameter 76.625 inches to 77.625 inches Airspeed Limits Normal operating limit Never exceed Flaps extended 0-20° 20° to fully extenced Landing gear extended 174 knots (200 MPH) 200 knots (230 MPH) I.A.S.
135 knots (155 MPH) I.A.S.
100 knots (115 MPH) I.A.S.
135 knots (155 MPH) I.A.S.
C.G. range (with (-0.14) to (+6.5) at 13,500 1bs.
landing gear (-6.35) to (+6.5) at 8,900 lbs. or less extended) Distances shown are plus (+) behind and minus (-) shead of the datum.
Straight line variation between points given.
Landing gear retraction moment +3180 in. Ib.
Maximun weight Takeoff 13,500 lbs., landing 13,150 lbe., zero fuel 13,527 Ibs. All waight in excess of 12,937 lbs.
must be fuel in outer wing tanks.
Maximum operating 17,000 ft. M.S.L..
altitude Minimum crew Two
FAA FORM 8110-2-1 (10-69) PAGE 7 OF1O PAGES
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA1368WE February 23, 1977 Fuel capacity 494 U. S. gallons (in wings) (usable) Two tanke 67 U.S. gallons cach (- 5.5) Two tanks 122 U.S. gallons each (+21.6) Two pairs of tanks 58 U.5. Gallons per pair (-4.56) Oil capacity 13 U.S. quarts per engine (-58.5) Serial Nos. All Series 2A and 2DA airplanes that are eligible Eligible for U.S. Airworthiness Certification under Type Certificate No. 816 and have been modified in accordance with FAA Sealed Aircraft Technical Service Summary Draving 828 Revision "T" or subsequent PAA Sealed revision. See NOTE 5.
Data Pertinent to ell Models Certification Basis Original Type Certificate No. A-816:
CAR Part 10 Modification covered by this STC:
(1) CAR 4b effective December 31,1953 plus Amendment 4b-1, or (2) "equal to or better than original CAR Part 10 certification" as appropriate, and (3) exemption No. 507 from CAR 40.443, dated October 7, 1966 and Special Condition outlined in Type Inspection Authorization No. T1754WE.
Previous dated of amendment: Novembe: 21, 1967 5. May 16, 1969 April 9, 1968 October 31, 1972
3. March 4, 1969 7. February 6, 1976
4. March 17, 1969 Required The following Aircraft Technical Service, Inc. Fea Equipment Approved Airplane Plight Manual for the de Havilland D.H. 114 Heron as modified by STC SA1368WE are required:
1. Series 2X Basic Configuration - Manual dated March 3, 1967.
2. Series 2X Configuration 2 - Manual dated March 3, 1967 with Revision dated November 21, 1967.
47.
PAGE 8 OF 10PAGES
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA13681E February 23, 1977
3. Series 2X Configuration B - Manual dated March 3, 1967 with Revision dated November 8, 1967.
4. Series 2A oz 2DA Configuration D - Series 2X Manual dated March 3, 1967 as revised April 9, 1968 to include Series 2A and 2DA at 12,499 lbs.
maximum weight. Series 2A or 2DA Manual dated July 26, 1968 required for operation at 13,500 lbs.
maxim takeoff weight.
5. Series 2A or 2DA Configuration C = Manual dated July 26, 1968.
6. Configuration A or C with Lycoming I0-540-KIC5 engines installed • Manual Supplement dated May 16, 1969 in addition to above noted Manual.
7. FAA Airplane Flight Manual Supplement dated February 23, 1977 is optional for use with propellers from 76.625 inches to 77.625 inches Airplane Flight Manual Supplements listed above show 77 inch propeller diameter only.
Refer to the applicable Aircraft Technical Service drawings show on Sumary Drawing 828 for additional equipment required as a result of the incorporation of this STC.
Service Information The de Havilland DaH. 114 Heron Maintenance and Repair Manual shown in the 'Required Equipment" section of Aircraft Specification A-816 must be retained for all portions of the airplane not modified by this STC.
Applicable FA Approved Lycoming and Hartzell maintenance and overhaul manuals must be substituted for the de lavilland engine and propeller manuals shown in A-816.
NOTE 1: Current weight and balance data including liet of equipment included in the certificated empty weight, and loading instructions, when necessary, must be provided for each aircraft at the time of airworthiness certification for retum to service.
FAA FORM 8110-2-1 (10-69) PAGE 9 OF 1OPAGES
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA1368WE Vebruary 23, 1977 NOTE 2: The maximm landing weight of Series 2X airplanes may be increased to 12,499 Ibs. when de Ravilland Heron Mod. 757 is incorporated.
Airplane Flight Kanual Revision, dated January 8, 1968, is required for operation at the higher landing weights permitted with Mod. 757.
NOTE 3: The maximum takeoff and landing weights of Series 24 or 2DA airplanes may be increased to 13,500 and 13,150 Ibs., respectively.
when an elevator down spring is installed in accordance with Aircraft Technical Service Drawing No. 1014, Zero fuel weight is 12,527 Ibs. and all weight in excess of 12,937 lbs. must be fuel in outer wing tanks. The applicable C.G. range at these Increased weights is:
(-0.14) to (+6.5) at 13,500 lbs.
(-6.35) to (+6.5) at 8,900 lba. ox less Series 2A or 2DA Manual dated July 26, 1968 is required for operation at these increased weights.
Engine Nos. 1 and 4 must incorporate the alternate 48 to l hydraulic pump drive ratio when engine driven pneumatic pumps are installed on those engines.
NOTE 5: Effective with Revision J, Aircraft Technical Service Summary Drawing No. 828 has been re-identified Riley Aeronautics Corp.
Drawing List No. 828.
NOTE 6: Deleted.
FAA FORM 8110-2-1 (10-69)
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