What it approves
Installation of AiResearch TPE 331 engines, increase in fuselage length and related changes.
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 SAL747VE This certificate issued to: Texas Airplene Mfg. Company, Inc.
P 0. Box 575 Addison, Texas 75001 Part * of the CIV11 ALT Regulations: #See page 5 of this STC for Certification Basis Original Product -Typebertificate Number: 307 Make: de Havilland Model: D.H. 104 Dove Series 7A, 8A, TAXC, BAXC Description of Type Design Change: Installation of AlRescareh TPE 331 engines, increase in fuselage length and related changes in accordance with FAA Sealed Von Carstedt Master Drawing List No. CPD9996 or FAA Sealed Revision thereto.
Limitations and Conditions: The limitations and conditions of Aircraft Specification No. A-807 apply except as outlined in pages 3 through 7 of this STC. A copy of this STC must be included in the permanent records of each airplane modified in accordance with this STG.
Date of Application: February 21, 1968 Date Reissued: Pebruary 26, 1973 Date of Issuance: July 23, 1968 Date Amended: 12/29/691 4/24/70; 5/27/70$ 11/14/73; 9/5/74 FEDERAL AVIATION By Direction of the Administrator don alone (Signature ) * MINISTRATO Don P. Watson Acting Chief, Engineering and Manufacturing Branch (Title)
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) September 5, 1974 Number SA1747WE
• Model D.H. 104 Dove Series 7A, 8A, 7AXC or 8AXC as modified by this STC (Normal Cateogry) Engines Two AiResearch TPE 331-55B or TPE 331-1-101E.
(Master Dwg. List No. CPD9996, Rev. Gor subsequent, is required for TPE 331-1-101E engines).
Fuel Fuels conforming to AiResearch Manufacturing Company of Arizona Report PE-5064-R. Not eligible for operation with aviation gasoli 0il MIL-L-23699 type oils conforming to AiResearch Manufacturing Company of Arizona Report PE-5065-R.
Engine Ratings (See NOTE 3 for applicable conditions).
Takeoff (5 min.) 605 equivalent shaft HP 575 shaft HP Maximum 529 equivalent shaft HP continuous 500 shaft HP Engine limits Propeller rpm 2000 maximum for steady state conditions 2100 maximum for 5 seconds transient overspeed 1920 minimum inflight cruise Torque Takeoff (5 min) 1512 Tb.ft.
Maximum 1390 lb.ft.
continuous Exhaust gas temperature (standard sea level day) TPE331-55B TPE331-1-101E Takeoff (5 min.) 1061°F (571°C) 1072°F (578°C) Maximum 983°F (530°C) 1029°F (554°C) continuous Starting Transient (one second) 1500°F (815°C) 1450°F (788°C)
47.
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate ontinuation Sheet) September 5, 1974 Number SAI7ATWE I - Model D.H. 104 Dove Series 7A, 8A, 7AXC or 8AXC as modified by this STC (Normal Cateogry) Engines Two AiResearch TPE 331-55B or TPE- 331-1-101E.
(Master Dwg. List No. CPD9996, Rev. G or subsequent, is required for TPE 331-1-101E engines).
Fuel Fuels conforming to AiResearch Manufacturing Company of Arizona Report PE-5064-R. Not eligible for operation with aviation gasolir 0il MIL-L-23699 type oils conforming to AiResearch Manufacturing Company of Arizona Report PE-5065-R.
Engine Ratings (See NOTE 3 for applicable conditions).
Takeoff (5 min.) 605 equivalent shaft HP 575 shaft HP Maximum 529 equivalent shaft HP continuous 500 shaft HP Engine limits Propeller rpm 2000 maximum for steady state conditions 2100 maximum for 5 seconds transient overspeed 1920 minimum inflight cruise Torque Takeoff (5 min) 1512 lb.ft.
Maximum 1390 1b.ft.
continuous Exhaust gas temperature (standard sea level day) TPE331-55B TPE331-1-101E Takeoff (5 min.) 1061°F (571°C) 1072°F (578°C) Maximum 983°F (530°C) 1029°F (554°C) continuous Starting Transient (one second) 1500°F (815°C) 1450°F (788°C)
FAA FORM 8110-2-1 (10-69) PAGES OF 7 PAGES
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate ontinuation Sheet) September 5, 1974 Number SA1747WE
- Model D.H. 104 Dove Series 7A, 8A, 7AXC or 8AXC as modified by this STC (Normal Cateogry) Engines Two AiResearch TPE 331-55B or TPE-331-1-101E.
(Master Dwg. List No. CPD9996, Rev. G or subsequent, 1s requirec for TPE 331-1-101E engines).
Fuel Fuels conforming to AiResearch Manufacturing Company of Arizona Report PE-5064-R. Not eligible for operation with aviation gasolir Oil MIL-L-23699 type oils conforming to AiResearch Manufacturing Company of Arizona Report PE-5065-R.
Engine Ratings (See NOTE 3 for applicable conditions).
Takeoff (5 min.) 605 equivalent shaft HP 575 shaft HP Maximum 529 equivalent shaft HP continuous 500 shaft HP Engine limits Propeller rpm 2000 maximum for steady state conditions 2100 maximum for 5 seconds transient overspeed 1920 minimum inflight cruise Torque Takeoff (5 min) 1512 Tb.ft.
Maximum 1390 1b.ft.
continuous Exhaust gas temperature (standard sea level day) TPЕ331-55B TPЕ331-1-101E Takeoff (5 min.) 1061°F (571°C) 1072°F (578°C) Maximum 983°F (530°C) 1029°F (554°C) continuous Starting Transient (one second) 1500°F (815°C) 1450°F (788°C) 47 PAGES OF 7 PAGES
*niced States of 2lmerica Department of Transportation Federal Aviation Administration Supplemental Type Certificate tinuation Sheet) September 5, 1974 _Number SA1747WE Maximum Baggage Forward baggage compartment maximum loading weight 200 1bs. Sta. 35.48 Aft baggage compartment maximum loading weight 600 1bs. Sta. 362 - 432* Fuel capacity 240 tanks 122 U.S. Gallons each (-3) 1635 1bs.
Fuel weight is based on 6.7 lbs. per gallon. See NOTE 1(b) Oil capacity 3 U.S. Gallons (-53) See NOTE 1(c) Control surface Elevator Up 26° 30' + 1° Down 13° 30' + 1° movements Elevator Trim Tab Up 10° + 0° 30' Down 21° + 0° 30' (Elevator Neutral) Rudder Right 25° + 1° Left 25° + 1° Rudder Trim Tab Right 18° · 0° 45' Left 18° # 0° 45' Aileron Up and Down 20° + 1° Aileron Trim Tab Up 17° + 0° 30' - Down 17° + 0° 30' Flaps Down 40° ‡ 1° Serial Numbers All series /A, 8A, VAC and SAXC airplanes that are eligible for Eligible U.S. Airworthiness Certification under Type Certificate No. 807.
See NOTE 5.
Data Pertinent to All Models Datum The datum plate, located 31.2 inches aft of the front leveling peg on the left side of the fuselage. Horizontal arms to the C.G. of the items shown on this specification are plus (+) behind and minus (-) ahead of the datum.
Leveling Means Datum pegs on left side of fuselage and datum pads on main spar in cabin.
Certification Original Type Certificate No. 807: CAR Part 10 Basis Modifications covered by this STC:
(7) For the powerplant installation - CAR Part 3 effective May 15, 1956, plus Amendments 3-1 through 3-8
FAA FORM 8110-2-1 (10-69) This certificate may be transferred in accordance with FAR 21.17.
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) September 5, 1974 Number SAI7A7WE The certificated empty weight and corresponding center of gravity locations must include system oil of one qt. total (-53) for both engines.
NOTE 2. Refer to Applicable FAA Approved Airplane Flight Manual for required place and instrument markings. All required placards must be installed in the appropriate locations.
NOTE 3. The ratings shown on this STC for the TPE331-55B engines are based on standard sea level conditions, compressor-inlet air 15°C and 29.92 in. Hg.
The takeoff and maximum continuous ratings shown for the TPE331-1-101E engines are available at sea level to 38.5°C and 43°C engine inlet tempera ture, respectively, or to 8,400 and 11,600 feet, respectively, on a standard temperature day. The ratings shown for either engine are based on dry inlet air, no external accessory loads, no air bleed or anti-icing airflow.
NOTE 4. The following aircraft parts are critical from the fatique standpoint and must be replaced at the time specified:
(1) Wing lower spar attach fittings - replace every 1800 hours time in service with new wing lower spar attach fittings, Von Carstedt . Part Number CPD-2004.
(2) Wing center section lower spar boom - replace every 1800 hours time in service in accordance with MOD 779 (See Hawker Siddeley Technical News Sheet Series CT(104) No. 119).
On completion of the modification specified in Airworthiness Directive AD 72-10-3 the service life of these parts is unlimited.
NOTE 5. The approval of this change in type design applies to the basic aircraft of the D.H. 104 Series models noted on page l of this STC that are otherwise unmodified. This approval should not be extended to other aircraft of these models on which other previously approved modifications are incorporated unless it is determined that the interrelationship between this change and any of those previously approved modifications will introduce no adverse effect on the airworthiness of the airplane.
FAA FORM 8110-2-1 (10-69) PAGE 7 OF 7 PAGES
ADs that name this STC · 3
An AD can apply because an STC is installed, or mention one in its text.