c Hamilton Sundstrand 

A United Technologies Company 

MAINTENANCE MANUAL 

14SF-5 

INFORMATION SUBJECT TO EXPORT CONTROL LAWS 

Subject to the EAR, ECCN 9E991. 

P5188 

This infonnation is subject to the export control laws of the United States, specifically including the Export Administration Regulations (EAR), 

15 C.F.R. Part 730 et. seq. Transfer, retransfer, or disclosure of this data by any means to a non-U.S. person (individual or company), 

whether in the United States or abroad, without any required export license or other approval from the U.S Government is prohibited, 

including without limitation any diversion to a military end user or use in a military end use application. 

VARIABLE PITCH AIRCRAFT 

PROPELLER 

MODEL NUMBER: 

14SF-5 

C1984, 1986,1991, 1994,1995, 1997,1999,2013 Hamilton Sundstrand Corporation 

PROPRIETARY 

THIS DOCUMENT AND THE INFORMATION CONTAINED HEREIN ARE THE PROPERTY OF HAMILTON SUNDSTRAND 

CORPORATION (HSC). RECIPIENT AGREES TO HOLD ALL SUCH INFORMATION IN CONFIDENCE AND AGREES IT SHALL BE 

USED ONLY FOR RECIPIENTS INTERNAL PURPOSES TO MAINTAIN RECIPIENTS EQUIPMENT OR AS MAY OTHERWISE BE 

PERMITTED IN AN APPLICABLE AGREEMENT BETWEEN RECIPIENT AND HSC. THIS DOCUMENT AND THE INFORMATION 

CONTAINED HEREIN SHALL NOT BE USED FOR ANY OTHER PURPOSE, INCLUDING THE CREATION, MANUFACTURE, 

DEVELOPMENT, OR DERNATION OF ANY REPAIRS, MODIFICATIONS, SPARE PARTS, DESIGN, OR CONFIGURATION CHANGES, 

OR TO OBTAIN FAA OR ANY OTHER GOVERNMENT OR REGULATORY APPROVAL FOR SAME. RECIPIENT AGREES NOT TO 

DISCLOSE SUCH INFORMATION TO ANY THIRD PARTY, EXCEPT AS MAY BE OTHERWISE PROVIDED FOR IN AN APPLICABLE 

AGREEMENT BETWEEN RECIPIENT AND HSC. COPYING OR DISCLOSURE OF THIS DOCUMENT AND THE INFORMATION 

CONTAINED HEREIN BY ANYONE WITHOUT HSC'S PRIOR WRITTEN PERMISSION IS NOT AUTHORIZED AND MAY RESULT IN 

CRIMINAL AND/OR CIVIL LIABILITY. 

The data in this document were developed only to mantain systems and/or parts manufactured by or for Hamilton Sundstrand or approved 

by Hamilton Sundstrand. The data may not be applicable to any other systems and/or parts, regardless of their apparent similarity to 

systems and/or parts manufactured by or for Hamilton Sundstrand or approved by Hamilton Sundstrand. Do not rely in any way on data in 

this document to maintain or oherwise support systems and/or parts that were not manufactured by or for Hamilton Sundstrand or approved 

by Hamilton Sundstrand without evidence that the Federal Aviation Administration or other regulatory agency has determined that the data 

in this document is valid for such use. 

PROPELLER SYSTEM MAINTENANCE MANUAL 

AIRWORTHINESS LIMITATIONS SECTION- FAA APPROVED 

REMAINDER OF MANUAL - FAA ACCEPTED 

Basic Issue: 

CAGE Code: 73030 61 Revision 1 0: 

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c Hamilton Sundstrand 

1. General 

A United Technologies Company 

MAINTENANCE MANUAL 

14SF-5 

AIRWORTHINESS LIMITATIONS 

A. The Airworthiness Limitations section is FAA approved and specifies maintenance 

required under§§ 43.16 and 91.403 of the Federal Aviation Regulations unless an 

alternative program has been FAA approved. 

2. Major Inspection Intervals 

A. Refer to the CHECK Section of Component Maintenance Manual 61-13-02 for 

instructions on how to do a Major Inspection (MI). 

B. The Major Inspection intervals are listed in Table AL-1 . It is the responsibility of the 

operator to monitor flight hours for each component listed in Table AL-1 and to make 

sure no component remains in service beyond its listed inspection interval time. 

C. In addition to the published operating time limits for blades and hubs, the requirement for 

repetitive Ml of these components will be no later than seven (7) years (or 84 months) 

since the Date Since Installation (DSI). The DSI will begin upon the initial installation 

after the most recent Ml or initial installation after production. 

D. Propeller blades and hubs must now be subjected to Ml based on published operating 

time limits for the component or 7 years from the DSI, whichever comes first. 

Table AL-1. Major Inspection Intervals 

INSPECTION INSPECTION 

ITEM PART NUMBER INTERVAL INTERVAL 

(FLIGHT HOURS) (CALENDAR TIME) 

Blade and Pin Assembly SFA13G1ROA, 10,000 7 Years 

SFA13M1ROA, 

SFA13M1POA, 

SFA 13U 1 ROA, 

SFA13U1POA 

Hub 782701-5, 782701-4 10,000 7 Years 

Outer Bearing Race* 782301-1 10,000 Not Applicable 

Inner Bearing Race 782303-1 10,000 Not Applicable 

(Two-Piece) 

Actuator Assembly 790180-2, 790180-3 10,000 Not Applicable 

*>>DCC<< The outer bearing race must be removed, discarded, and replaced at each 

inspection interval (see the CHECK Section of Component Maintenance Manual 61-13-02). It 

is permissible to use the propeller hub time to track the total time of the outer bearing race. 

Use or disclosure of this data is subject to restrictions on the Trtle Page of this document. 

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3. Critical Part Inspections 

A United Technologies Company 

MAINTENANCE MANUAL 

14SF-5 

A. The components listed in Table AL-2 require inspection to assure continued 

airworthiness. Component assemblies must be removed from service and subjected to 

the required inspections. 

B. Critical Part Inspections accomplished in accordance with the CHECK section of the 

applicable Component Maintenance Manual, at the intervals given in Table AL-2, satisfy 

the requirements of Airworthiness Directive (AD) 96-25-20 as an alternate method of 

compliance as approved by letter from the manager, FAA Boston Aircraft Certification 

Office, on June 3, 1999. 

C. It is the responsibility of the operator to monitor the flight hours for each component 

listed in Table AL-2. 

Table AL-2. Propeller Components With Mandatory Inspections 

ITEM PART NO. INSPECTION INTERVAL 

(FLIGHT HOURS) 

Acty~tor A§§!i!mbl~* 790180-2, 790180-3 Maximum 10,500 hour 

intervals 

Qil Tll!O§f!i!r T!.!b!i! ~od 814829-1 Initial Inspection*** within 

Retainer* 782515-1 6000 hours or three years 

after the effective date of AD 

96-25-20 (February 7, 1997) 

Repeat InspectionMaximum 10,500 hour 

intervals 

PrQ!2!i!ll!;!r QQntrQI Unit** (PQ!.!) 782490-6, A6, -11, A11, -18, Initial Inspection*** within 

A 18, -29, A29, -40, A40, -51, 6000 hours or three years 

A51 after the effective date of AD 

96-25-20 (February 7, 1997) 

Repeat InspectionMaximum 10,500 hour 

intervals 

*Do the inspections for these components in accordance with Component Maintenance Manual 61-13-02. 

The tube may be inspected using this Maintenance Manual. 

** Do the inspections for these components in accordance with Component Maintenance 

Manual61-21-07. 

***Parts manufactured after the effectivity of date of AD 96-25-20 (February 7, 1997) have met the initial 

inspection requirement (paragraph 2.(a)) by an alternate method of compliance as approved by letter from 

the manager, FAA Boston Aircraft Certification Office, on June 3, 1999. 

Use or disclosure of this data is subject to restrictions on the ntie Page of this document 

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c Hamilton Sundstrand 

A United Technologies Company 

MAINTENANCE MANUAL 

14SF-5 

4. Ballscrew Spline Inspection 

A. The internal spline of the ballscrew in the PC Us listed in Table AL-3 requires inspection 

to assure continued airworthiness. Component assemblies must be removed from 

service and be subjected to the required inspections at intervals established in 

AD 95-22-12. The intervals are based on the time since new or time since last 

inspection. Do the inspection in accordance with the CHECK section of Chapter 

61-22-00 (Propeller Control and Adapter). 

B. It is the responsibility of the operator to monitor the flight hours for the PCU. 

Table AL-3. Propeller Control Unit Components With Mandatory Inspections 

ITEM PART NUMBER INSPECTION INTERVAL 

(FLIGHT HOURS) 

Propeller Control Unit (PCU) 782490-6, A6, -11 , A11, -18, A18 See Airworthiness Directive 

(Without Quill Damper, and 95-22-12 

without Secondary Drive Quill) 

Propeller Control Unit (PCU) 782490-29, A29 and PCUs with See Airworthiness Directive 

(With Quill Damper, and the marking "SB14SF-61-67" on 95-22-12 

without Secondary Drive Quill) the Identification Plate 

5. PCU Primary Quill Torque Check 

A. The PCU Part Numbers listed in Table AL-4 are equipped with a secondary drive quill 

and require an inspection to assure continued airworthiness. Component assemblies 

must be subjected to the required inspection at intervals established in AD 95-22-12. 

The intervals are based on the time since new or time since last inspection. Do the 

inspection in accordance with the CHECK section of Chapter 61-22-00 (Propeller 

Control and Adapter). 

B. It is the responsibility of the operator to monitor the flight hours for the PCU. 

Table AL-4. Propeller Control Unit Components With Mandatory Inspections 

ITEM PART NUMBER INSPECTION INTERVAL 

(FLIGHT HOURS) 

Propeller Control Unit (PCU) 782490-40, A40, -51, A51 See Airworthiness Directive 

95-22-12 

6. Special Instructions 

A. If there is evidence of overspeed, foreign object damage, lightning damage, or 

overtorque, do the inspection procedures in paragraphs 6., 7., 8., and 9. in Chapter 61-

10-00, CHECK, in this manual. Complete the appropriate form (Figure 502, Figure 504, 

or Figure 505) and send a copy to the Hamilton Sundstrand address specified on it. 

Also, if necessary, make sure that a report of the incident is provided to the Federal 

Aviation Administration (FAA) in accordance with FAR 21.3 requirements. 

Use or disclosure of this data is subject to resbictions on the Title Page of this document. 

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c Hamilton Sundstrand 

A United Technologies Company 

MAINTENANCE MANUAL 

14SF-5 

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Use or disclosure of this data is subject to restrictions on the Titie Page of this document 

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