# TCDS A8EU: Robertson Cliff c/o Gadbois Business Management - Type: Type certificate data sheet - Status: Current - Holder: Robertson Cliff c/o Gadbois Business Management - Revision: 0 - Revised: February 7, 1966 - Product: Aircraft, Small Airplane - Certification basis: Part 21 - Data sheet PDF: https://openairdocs.org/files/sha256/c8/ca/c8cacda547fcb96d310c6a7c669267f0a0cd5cd7a32d72ed706e92f808a04684 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/55EF6EA600A27B50852567320065303C.0001 - Page: https://openairdocs.org/tcds/A8EU ## Models (1) As the data sheet lists them. - D.H.82A Tiger Moth ## 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 Rev. No. - - - Reformatted 1/95. FEDERAL AVIATION AGENCY A8EU DE HAVILLAND DH 82A February 7, 1966 TYPE CERTIFICATE DATA SHEET NO. A8EU This data sheet which is a part of type certificate No. A8EU 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 Cliff Robertson c/o Gadbois Business Management 9201 Wilshire Boulevard Beverly Hills, California I - De Havilland Model DH 82A 2POLB (Normal and Utility Category), approved February 7, 1966. Engine Bristol Siddeley Gipsy Major 1, or 1F, or 1C or 1J. Fuel Gipsy Major 1 - Minimum grade 69 Octane. Unleaded. Gipsy Major 1F - Minimum grade 69 Octane (Maximum lead content 3.33 milliliters (mls) Tetraethyl lead (TEL)/US gallon. Gipsy Major 1C - Minimum grade 77 Octane. Maximum lead content 3.33 mls. TEL/US gallon. Gipsy Major 1J - Minimum grade 80 Octane. Maximum lead content 3.33 mls. TEL/US gallon. Engine limits Gipsy Major 1 - Maximum continuous (Sea level) 2100 rpm (122 b.h.p.) and 1F Maximum take-off 2100 rpm (122 b.h.p.) Maximum overspeed, full throttle, (5 minutes limit) 2350 rpm. Gipsy Major 1C - Maximum continuous (Sea level) 2100 rpm (130 b.h.p.) Maximum take-off 2100 rpm (130 b.h.p.) Maximum overspeed, full throttle, (5 minutes limit) 2400 rpm. Gipsy Major 1J - Maximum continuous (Sea level) 2400 rpm (142 b.h.p.) Maximum take-off 2400 rpm (142 b.h.p.) Maximum overspeed, full throttle, (5 minutes limit) 2550 rpm. Propellers Gipsy Major 1, 1F and 1J Propellers Fixed Pitch Manufacturers Drg. No. Diam. (ft) Pitch. (ft) WESTLAND 67104A/X4 7.00 4.77 " 67104A/X10 7.00 4.60 " 67104A/X12 7.00 5.18 " 67104A/X14 7.00 4.52 " 67575A/X1 7.00 4.71 " 84723A/X1 7.00 4.84 " A66016/X4 7.00 4.58 " A66938/X2 7.50 3.52 " A104940/X2 7.42 3.52 " A104940/X3 7.42 3.70 " A104943/X3 7.17 3.62 " C66969/X1 5.92 4.50 DE HAVILLAND DH5212/D 6.17 5.42 " DH5218/B 6.50 5.10 A8EU 2 Propellers (cont'd) Gipsy Major 1, 1F and 1J (cont'd) Propellers Fixed Pitch Manufacturers Drg. No. Diam. (ft) Pitch. (ft) " DH5220/B 6.33 5.08 " DH5220/G 6.33 4.58 " DH5220/H 6.33 4.92 " DH5220/L 6.33 4.75 " DH5220/M 6.33 4.50 " DH5220/P 6.33 4.58 " DH5232/A 6.50 5.10 " DH5232/B 6.50 5.30 " DH5234/A 6.75 5.08 " DH5234/B 6.75 4.95 " DH5234/J 6.75 4.40 HORDERN RICHMOND 6.84 3.53 LANG LA506/3 6.50 4.35 " LA594/2 6.50 4.35 " LA596 6.50 5.00 " LA604 6.50 4.58 AIRSCREW-WEYROC Z973 6.23 5.50 " Z978 5.85 5.50 " Z8010 6.84 3.53 " ZD5220/1 6.33 4.83 Gipsy Major 1C WESTLAND B104951/X2 6.75 5.02 DE HAVILLAND DH5220/P 6.33 4.58 AIRSCREW-WEYROC Z8010 6.84 3.53 WESTLAND A66875/X4 6.50 5.84 Airspeed limits Maximum Structural cruising 115 m.p.h. (100 knots) Never exceed 160 m.p.h. (139 knots) C.G. range (+7.0) to (+13.5) when anti-spinning strips are not fitted. When anti-spinning strips are fitted on each side of the rear fuselage (+7.0) to (+15.3) under ordinary flight conditions, (+7.0) to (+13.5) under instrument flight rule conditions. Datum Leading edge of lower mainplane at root. Leveling means Longitudinal: Straight-edge on the studs on the outside of the fuselage right hand top longeron. Lateral: Straight-edge clamped to underside of left hand and right hand top longerons in the front cockpit. Maximum weight 1825 lbs. (Normal Category) 1770 lbs. (Utility Category) No. of seats 2 (1 at +16.0, 1 at +46.0) Maximum baggage 50 lb (+75.0) Fuel capacity 23 U.S. gal. (1 tank in upper mainplane at -8.3), or 29 U.S. gal. (1 tank in upper mainplane at -8.3). 12 U.S. gal. auxiliary (1 tank in fuselage at -11.66) Oil capacity 2.5 U.S. gal. (-13.3) Control surface Elevator: Up 11 1/2 + 3/4 inches at T.E. movements Down 8 + 1/2 inch at T.E. Rudder: 14 1/2 inches left and right at T.E. Ailerons: 8 inches up at T.E. 1 1/4 inches down at T.E. Slat travel: 3 1/4 inches 3 A8EU Certification basis FAR 21.29 (FAA letter August 19, 1965) Type Certificate No. A8EU issued February 7, 1966. Date of Application for Type Certificate December 11, 1965. Import Requirements A U.S. Airworthiness Certificate may be issued on the basis of a United Kingdom Certificate of Airworthiness for Export in the Transport Category (Passengers) signed by a representative of the Ministry of Aviation containing the following statement: "The airplane covered by this certificate has been examined, and found to meet the airworthiness requirements of the United Kingdom and conforms to Type Certificate No. A8EU." Serial Nos. eligible A United Kingdom Certificate of Airworthiness for Export endorsed as noted under Import Requirements, must be submitted for each individual aircraft for which application for U.S. Airworthiness Certificate is made. The U.K Certificate of Airworthiness for Export is valid as a basis for issuance of the U.S. airworthiness certificate for a period of 60 days. If application for U.S. certification is made after 60 days from the date of issuance of the U.K. export certificate, this certificate must be reissued. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in the aircraft for certification. NOTE 1. Current weight and balance report, including list of equipment in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. NOTE 2. The following placards must be displayed: (1) "Speed must not exceed 139 knots (160 m.p.h.) (2) Engine limitations: (a) Gipsy Major 1 or 1F. "Normal full r.p.m. 2100 Max. permissible for not more than 5 mins. 2350 r.p.m." (b) Gipsy Major 1C. "Normal full r.p.m. 2100 Max. permissible for not more than 5 mins. 2400 r.p.m." (c) Gipsy Major 1J. "Normal full r.p.m. 2400 Max. permissible for not more than 5 mins. 2550 r.p.m." (3) "Smoking prohibited." (4) "Normal Category Maximum design weight 1825 lbs. No acrobatic maneuvers including spins approved." (5) "Utility Category Maximum design weight 1770 lbs. No acrobatic maneuvers approved except those listed below Maneuver Entry Speed Chandelles 120 m.p.h. (105 knots) Lazy Eights 120 m.p.h. (105 knots) Steep Turns 92 m.p.h. ( 80 knots) Stalls (except whip stalls) Slow deceleration Spins Slow deceleration NOTE 3. The airplane must be assembled in accordance with the rigging instructions of the De Havilland Maintenance Manual. NOTE 4. The airplane must be flight checked after assembly. .....END..... ``` ## ADs (2, in force first) - [AD 2014-24-01](https://openairdocs.org/ad/2014-24-01): Fuselage, Wing Attach Fittings · de Havilland D.H.83 Fox Moth, D.H.82A Tiger Moth and DH 82A. Effective Jan 6, 2015 - [AD 2014-17-09](https://openairdocs.org/ad/2014-17-09): Fuselage, Wing Attach Fittings · Williams Harry E. D.H.83 Fox Moth, D.H.82A Tiger Moth and DH 82A. Effective Sep 18, 2014 ## STCs approved under this data sheet (21) - [STC SA03898NY](https://openairdocs.org/stc/SA03898NY): Installation and maintenance of ORATEX covering and coating material. Aircraft Design & Certification Ltd - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc. - [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley - [STC SA00192LA](https://openairdocs.org/stc/SA00192LA): Replacement of BTH AG4 impluse and nonimpulse magnetos with Slick Magnetos on Gipsy I, Gipsy II, and Gipsy III model engines and Gipsy major series 1 through 10MK2 model engines.. Moth Aircraft Company - [STC SA2558NM](https://openairdocs.org/stc/SA2558NM): This approval authorizes the modification of the DeHavilland aircraft co LTD piston, P/N 2200-25/2.. Moth Aircraft Company - [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc. - [STC SA02283SE PAGE 1](https://openairdocs.org/stc/SA02283SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc. - [STC SA02402SE PAGE 1](https://openairdocs.org/stc/SA02402SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc. - [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc. - [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc. - [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc - [STC SA01157LA](https://openairdocs.org/stc/SA01157LA): Installation of Electronics International Model FP-5 or FP-5L fuel flow/fuel pressure instrument as a replacement instrument.. Electronics International Inc. - [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc. - [STC SA00697SE](https://openairdocs.org/stc/SA00697SE): Assemble wood structure using System Three Resins, Inc. T-88 epoxy adhesive. Install temperature monitoring system in upper wing and cockpit placard.. Miltner Harry - [STC SA00435SE](https://openairdocs.org/stc/SA00435SE): Installation of Concord 35RG battery, Rotax N3EY C.W. starter, Cessna part no W-R/RBM solenoid, Niehoff Part No. UN401 push button starter switch, stainless steel battery box, and starter circuit wiring and components. Installation of Scott 3200 steerable tailwheel, leaf spring, and tailwheet steering linkage chains and springs. Installation of Cleveland master brake cylinders Model 10-35, Cleveland part no 164-01700 brake discs, Cleveland Part No. 030-07500 brake calipers, and aluminum and braided stainless steel brake lines and fittings. Installation of Sensenitch W79CFL-60 propeller.. Miltner Harry - [STC SA1626NM PAGE 1](https://openairdocs.org/stc/SA1626NM%20PAGE%201): Installation of Electronics Int'l Digital EGT/CHT Instruments and accessories. (201 Series). Electronics International - [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International - [STC SA1351WE](https://openairdocs.org/stc/SA1351WE): Replace existing fabric on wings, fuselage, empennage, and/or control surfaces, with Ceconite101 material. (262A Series -12). Ceconite Inc - [STC SA2666L](https://openairdocs.org/stc/SA2666L): Covering of Ceconite 102 material on wings, fuselage and empennage.. Ceconite, Inc --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.