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P886
Revision 18

SENSENICH 74D

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December 14, 1995

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Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P886) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations provided they are installed, operated and maintained as prescribed by the approved manufacturer's manuals and other approved instructions.

Type Certificate Holder:	Sensenich Propeller Manufacturing Company, Inc.
	14 Citation Lane
	Lititz, PA 17543

Type Fixed-Pitch Metal
Material Aluminum Alloy
Number of Blades Two

Basic Model

Takeoff &

Standard

Hub Drilling

Hub Dimensions

Weight

(See Note 2)

Max. Cont.

Diameter

Pitch

No.

Dia.

Dia. Bolt

Dia.

Thick.

(lb.)

HP

RPM

Holes

Holes

Circle

(Max. Dia.)

74DM6

165

2800

74"

68"-48"

6

25/64"

4-3/4"

6"

3-7/16"

32.4

74DM7

165

2800

74"

68"-48"

6

29/64"

4-3/4"

6"

3-7/16"

32.4

Deleted December 14, 1995, See Note 2

Deleted December 14, 1995, See Note 2

74DR

165

2800

74"

68"-48"

8

25/64"

5-1/4"

6-1/2"

3-7/16"

29.5

Deleted December 14, 1995, See Note 2

74DC

165

2800

74"

68"-50"

6

33/64"

4"

5-1/2"

3-7/16"

31.1

Deleted December 14, 1995, See Note 2

Certification Basis CAR 14 effective March 5, 1952, as amended by 14-1 effective May 16, 1953. Type Certificate No. 886 issued June 29, 1954, revised April 9, 1959. Date of application for Type Certificate April 27, 1954.

Production Basis Production Certificate No. 1NE

NOTE 1. Installation. These models are for installation on flanged propeller shaft ends (see NOTE 2). Installation is to be made with special steel bolts which are furnished or specified by the propeller manufacturer in accordance with the appropriate propeller assembly drawing. See NOTE 7 for spacer designations and NOTE 9 for approved spacer lengths.

• a. Propeller Model 74DC is installed on SAE ARP-502 flanged shaft.
  
• b. Propeller Model 74DR is installed on SAE No. 3 flanged shaft.
  
• c. Propeller Model 74DM6 is installed on SAE No. 2 flanged shaft with 3/8 inch diameter attaching bolts and 5/8 inch diameter drive bushings.
  
• d. Propeller Model 74DM7 is installed on SAE No. 2 flanged shaft with 7/16 inch diameter attaching bolts and 5/8 inch diameter drive bushings.
  

P886 -2-

Revision 17

NOTE 2. Model Designation.

NOTE 3, 4, 5, 6, and 8. Not applicable.

NOTE 7. Spacers. Sensenich spacer models are identified by flange codes (see NOTE 2) and spacer thickness designated based on multiples of 1/4 inch. See NOTE 9 for approved spacer lengths.

NOTE 9. Special Limits. Table of Propeller-Engine Combinations

Approved Vibrationwise for Use on Normal Category Single-Engine Tractor Aircraft

The maximum and minimum propeller diameters that can be used from a vibration standpoint are shown below. No reduction below the minimum diameter listed is permissible since this figure includes the diameter reduction allowable for repair purposes.

Propeller		Engine		Max. Dia.		Min. Dia.
Model		Model		(Inches)		(Inches)		Placards
74DM6, 74DM7 Spacers 0 to 3.5 inches incl.		Lycoming O-320 Series 160 h.p. @ 2700 r.p.m. or less.		74		72		None
74DM6, 74DM7 Spacers 0 to 3.5 inches incl.		Lycoming O-290-D, -D2, and -D2B Series		74		72		None
74DC		Franklin 6A4-150-B4		74		72		Avoid continuous operation between 2150 & 2250 r.p.m. on ground and in flight
74DR		Franklin 6A4-165-B3		74		72		Avoid continuous operation between 2150 & 2250 r.p.m. on ground and in flight
74DC		Franklin 6A4-165-B4		74		72		Avoid continuous operation between 2150 & 2250 r.p.m. on ground and in flight
74DR-1		Continental C-125-2		73		71		None
74DR		Continental C-145 Series and Continental O-300-A, -B, 145 h.p. @ 2700 r.p.m. or less.		74		72		None
74DC		Continental O-300-C, -D, and -E, 145 h.p. @ 2700 r.p.m. or less		74		72		None
74DC		Continental IO-346-A 165h.p. @ 2700 r.p.m. or less.		74		74		None

NOTE 10. Special Notes. The work "eligible" as used herein does not signify approval. For approval, compliance with the applicable aircraft airworthiness requirements is necessary.

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