STC SA2555NM

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA2555NM This certificate issued to: Robert C. Sheldon Purt 3 of the Civil Air

•Regulutions effective May 15, 1956 and Paragraph 3.11? as amended Oct 1, 1959.

Original Product -Type Pertificate Number: 3A21 Make: Cessna Murtel: T210L 'scriplin/ Jype Desiy» thunge: Installation of Continental TS10-520-R engine, McCauley D3A34C402/90DFA-10 propeller and associated installation components in accordance with FAA sealed Robert C. Sheldon Installation Instructions dated 17 January 1985 or later FAA sealed revisions.

Limitations and Conditions: The approval of this change in type design applies to the basic aircraft of the specified models 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 by the installer that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of that aircraft. Supplemental Type Certificate Addendum No.

, SA2555N is a part of this Supplemental Type Certificate.

Date of Application: 14 April 1982 Date Reissued:

22 January 1985 Date Amended:

AVIATION Marvin 7. Kammelea By Direction of the Administrator (Signature) for CHARLES I. BLOMER, Manager Western Aircraft Certification Office (Title) 47 FAA FORM 8110-2 (10-68) Page 1 of 4 Pages

(1) 1-22-85 Number SA2555NM Supplemental Type Certificate ADDENDUM NO. SA2555NM The conditions and limitations of Type Certificate Data Sheet No. 3A21 apply except as follows:

This Addendum, which is part of Supplemental Type Certificate No. SA2555NM, prescribes conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Civil Air Regulations.

A copy of this Addendum shall be maintained as part of the modified aircraft's permanent records.

I - Model T210L, 6PCLM (Normal Category), modified per STC SA2555NM Engine Continental TSI0-520-R Engine Limits Takeoff (5 min.) at 2700 RPM, 36.5 in. Hg mp (310 hp) Maximum Continuous at 2600 RPM, 35.0 in. Hg mp (285 hp) Propeller and McCauley Constant Speed Propeller Limits Hub Model: D3A34C402 Blade Model: 90DFA-10 Diameter: not over 80 inches not under 78.5 inches Pitch settings at 30 inch station:

low 12.4° high 28.5° Spinner: Cessna P/N 1250419K200 or 1250419-10 Powerplant Instrument Minimum Normal Caution Maximum Markings (See NOTE 2) Red Radial Green Are Yellow Arc Red Radial Manifold Pressure 15.0-30.0 35.0-36.5 36.5 (PSI) Tachometer 2150-2600 1850-2150 2700 (RPM) 2600-2700 Fuel Flow (PSI) 3.5 19.8

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(1) 1-22-85 Number: SA2555041 Supplemental Type Certificate ADDENDUM NO. SA2555NM (cont.)

Serial Nos. Eligible 21059503 thru 21061573 Required Equipment In addition to the equipment applicable and required by Type Certificate Data Sheet No. 3A21, the equipment specified in FAA sealed Robert C. Sheldon Installation Instructions dated 17 January 1985 or later FAA sealed revisions as a result of incorporating STC SA2555NM.

NOTE 1. Current weight and balance report including list of equipment included in the certificated empty weight, and loading istructions when necessary, mut be in the airplane.

NOTE 2. The following information shall be provided to the pilot in the form of placards or markings:

a. Adjacent to tachometer- "AVOID CONTINUOUS OPERATION BETWEEN 1850 AND 2150 RPM ABOVE 24 IN. MP"

b. Near the engine power instruments - "MAXIMUM POWER SETTING & FUEL FLOW T.O. (5 min. only): 2700 r.p.m. Normal climb: 2500 r.p.m.

36.5 in. mp., 186 1bs/hr Max. continuous power: 2600 r.p.m.

Alt-ft/1000 Mp.-in. hg Fuel flow-lbs/hr In addition to the placards specified above, the prescribed operating limitations in "Powerplant Instrument Markings" on this STC Addendum must also be displayed by permanent markings.

NOTE 3. Noise Characteristics: This modification results in no acoustical change, as defined in paragraph 21.93(b) of the Federal Aviation Regulations.

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