c Hamilton Sundstrand 

A United Technologies Company 

MAINTENANCE MANUAL 

14SF-7 

Information Subject to Export Control Laws 

P5185 

The technical data In this document (or file) Is controlled for export under the Export Administration Regulations (EAR), 15 CFR 

Parts 730-774. VIolations of these laws may be subject to fines and penalties under the Export Administration Act. 

EAR Export Classification: ECCN 9E991 

VARIABLE PITCH AIRCRAFT 

PROPELLER 

MODEL NUMBER: 

14SF-7 

© 1984, 1986-1988, 1993-1995, 1997, 1999, 2006, 2011 Hamilton Sundstrand Corporation 

PROPRIETARY 

THIS DOCUMENT AND THE INFORMATION CONTAINED HEREIN ARE THE PROPERTY OF HAMIL TON SUNDSTRAND 

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

USED ONLY FOR RECIPIENT'S INTERNAL PURPOSES TO MAINTAIN RECIPIENT'S 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 DERIVATION 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 OTHERWISE BE 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 WRITIEN PERMISSION IS NOT AUTHORIZED AND MAY RESULT IN 

CRIMINAL AND/OR CIVIL LIABILITY. 

The data in this document were developed only to maintain 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 otherwise 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 

CAGE Code: 73030 61 

Page T-1 

Basic Issue: Jun 15/84 

Revision 13: Dec 13/11 
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A United Technologies Company 

MAINTENANCE MANUAL 

14SF-7 

AIRWORTHINESS LIMITATIONS 

1. General 

A. The airworthiness limitations section is FAA approved and specifies maintenance 

required to be followed when complying with §§ 43.16 and 91.403 of the Federal 

Aviation Regulations unless an alternative program has been FAA approved. 

2. Critical Part Inspections 

A. The components listed in Table AL-1 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-1, 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-1. 

Table AL-1. Propeller Components With Mandatory Inspections 

ITEM PART NO. INSPECTION INTERVAL 

(FLIGHT HOURS) 

Actuator Assembly* 790180-3, -2 Maximum 10,500 hour 

intervals 

Oil Transfer Tube and 814829-1 Initial Inspection***- within 

Retainer* 782515-1 6,000 hours or 3 years after 

the effective date of AD 96-

25-20 (February 7 ,1997) 

Repeat Inspection -

Maximum 10,500 hour 

intervals 

Propeller Control Unit** (PCU) 782490-5, A5, -9, A9, -10, A10, Initial Inspection***- within 

-14, A14, -17, A17, -28, A28, 6,000 hours or 3 years after 

-39, A39, -50, A50 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 oil transfer tube can be inspected using Maintenance Manual P5185. 

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

Manual 61-21-03. 

*** Parts manufactured after the effectivity 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 TiUe Page of this document. 

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A United Technologies Company 

MAINTENANCE MANUAL 

14SF-7 

3. Ballscrew Spline Inspection 

A. The internal spline of the ballscrew in the PC Us listed in Table AL-2 requires inspection 

to assure continued airworthiness. Component assemblies must be removed from 

service and 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-2. Propeller Control Unit Components With Mandatory Inspections 

ITEM PART NUMBER INSPECTION INTERVAL 

Propeller Control Unit (PCU) 782490-5, AS, -9, A9, -10, See Airworthiness 

(Without Quill Damper, and A10, -14, A14, -17, A17 Directive 95-22-12 

without Secondary Drive Quill) 

Propeller Control Unit (PCU) 782490-28, A28, and PCUs See Airworthiness 

(With Quill Damper, and with the marking Directive 95-22-12 

without Secondary Drive Quill) "SB14SF-61-67" on the 

Identification Plate 

4. PCU Primary Quill Torque Check 

A. The PCU Part Numbers listed in Table AL-3 are equipped with a secondary drive quill 

and require an inspection to assure continued airworthiness. Component assemblies 

must 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. 

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) 782490-39, A39, -50, A50 See Airworthiness Directive 

95-22-12 

5. Special Instructions 

A. If there is evidence of overspeed, overtorque, impact damage, or lightning hits, then do 

the applicable inspection in accordance with the referenced paragraphs below. Upon 

completion of the applicable inspection, complete the appropriate form (see Figure 502, 

Figure 503, and Figure 504 in the CHECK section of Chapter 61-1 0-00). 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. Also in the CHECK section of Chapter 

61-10-00: 

Use or disclosure of this data Is subject to restrictions on the T!tie Page of this document. 

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• Refer to paragraph 6, lnspectjon/Checks After Overspeed, of the CHECK section of 

Chapter 61-10-00. 

• Refer to paragraph 7, Inspection/Checks After Oyertorgye, of the CHECK section of 

Chapter 61-10-00. 

• Refer to paragraph 8, Inspection After Impact, of the CHECK section of Chapter 61-

10-00. 

• Refer to paragraph 9, Inspection After Lightning $trikes, of the CHECK section of 

Chapter 61-10-00. 

6. Major Inspection Interval 

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

on how to do a major inspection. 

B. The major inspection intervals in operating hours are listed in Table AL-4. It is the 

responsibility of the operator to monitor flight hours for each component listed in Table 

AL-4 and to make sure that 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-4. Major Inspection Intervals 

INSPECTION INSPECTION 

ITEM PART NUMBER INTERVAL INTERVAL 

(FLIGHT HOURS) (CALENDAR TIME) 

Hub 782701-4, 782701-5 10,500 7 Years 

Outer Bearing Race* 782301-1 10,500 Not Applicable 

Inner Bearing Race 782303-1 10,500 Not Applicable 

(two-piece) 

Blade and Pin Assembly SFA13G1ROA, 10,500 7 Years 

SFA13M1ROA, 

SFA 13M 1 POA, 

SFA 13U 1 ROA, 

SFA13U1POA 

Actuator Assembly 790180-2, 790180-3 10,500 Not Applicable 

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

inspection interval (see CHECK section of Component Maintenance Manual61-13-02). 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 TIHe Page of this document 

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A United Technologies Company 

MAINTENANCE MANUAL 

14SF-7 

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

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