MAINTENANCE MANUAL

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TO ALL HOLDERS OF HAMILTON SUNDSTRAND’S

MAINTENANCE MANUAL P5189

APPLICABILITY: CN 235

THIS SHEET TRANSMITS REVISION NO. 8 DATE FEB 20/13

HIGHLIGHTS

We recommend that you put this revision into your manual without delay. After you have put the 

revised pages in your manual, mark the Record of Revisions sheet with the new revision number and 

date, and write the date that you insert the revised pages into your manual and your initials on the 

Record of Revisions sheet in the appropriate spaces.

The revised pages of this manual were reprinted. Please replace these pages of your manual with 

the pages of this revision. General format and layout changes were made in addition to these 

technical changes:

If you have questions about this manual, you can contact Technical Publications by email at 

mailto:tech.pubs@hs.utc.com or fax at (860) 660-9014.

The changes made to the manual during this revision are described in the table that follows:

Page Description of Change Change Driver References

T-1 Revised Export Control statement. Non-technical change; 

no substantiation required

AL-1 thru AL-4 Updated format to latest version and added 

7 year major inspection interval column to 

Table AL-1. Added footnote to table AL-1. 

Revised paragraph 7.

SIR: 14RF-21-023

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Basic Issue:

Revision

MAINTENANCE MANUAL

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P5189

VARIABLE PITCH AIRCRAFT 

PROPELLER SYSTEM

PROPELLER SYSTEM MAINTENANCE MANUAL

14RF-21 PROPELLER MODEL 

PART NUMBER:

782750-3

782750-4

782750-5

782750-6

782750-7

782750-8

782750-12

AIRWORTHINESS LIMITATIONS SECTIONS - FAA APPROVED

REMAINDER OF MANUAL - FAA ACCEPTED

Feb 20/13

Jan 15/83

8:

© 1983, 1987, 1994, 1995, 1998, 2006, 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 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 WRITTEN PERMISSION IS NOT AUTHORIZED AND MAY RESULT IN 

CRIMINAL AND/OR CIVIL LIABILITY.

WARNING - ITAR STATEMENT 

THIS DOCUMENT OR FILE CONTAINS TECHNICAL DATA THE EXPORT OF WHICH IS, OR MAY BE, RESTRICTED BY 

THE ARMS EXPORT CONTROL ACT AND THE INTERNATIONAL TRAFFIC IN ARMS REGULATIONS (ITAR), 22 

C.F.R. PARTS 120 - 130. DIVERSION CONTRARY TO U.S. LAW IS PROHIBITED. THE EXPORT, RE-EXPORT, TRANSFER OR RE-TRANSFER OF THIS TECHNICAL DATA TO ANY OTHER COMPANY, ENTITY, PERSON, OR DESTINATION, OR FOR ANY USE OR PURPOSE OTHER THAN THAT FOR WHICH THE TECHNICAL DATA WAS ORIGINALLY 

PROVIDED BY HAMILTON SUNDSTRAND, IS PROHIBITED WITHOUT PRIOR WRITTEN APPROVAL FROM HAMILTON SUNDSTRAND AND AUTHORIZATION UNDER APPLICABLE EXPORT CONTROL LAWS. 

ITAR/USML: VIII(i) 
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P5189

AIRWORTHINESS LIMITATIONS

1. General

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 61-13-03 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 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 MI 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 MI or initial installation after production. 

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

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

Table AL-1. Major Inspection Intervals

ITEM PART NUMBER

INSPECTION 

INTERVAL

(FLIGHT HOURS)

INSPECTION 

INTERVAL

(CALENDAR 

TIME)

Actuator Assembly 790199-2, 790199-3, 790199-5, 

790199-6, 790199-8

6,500 Not Applicable

Hub 782501-4, 782501-6, 814721-1, 

782501-7, 814721-2

6,500 7 Years

Outer Bearing 

Race*

782674-1 6,500 Not Applicable

Inner Bearing Race

(two-piece)

782676-1

782675-1

6,500 Not Applicable

Blade and Pin 

Assembly

RFC11L1R0C, RFC11P1R0C, 

RFC11R1R0C, RFC11V1R0C, 

RFC11V1P0C, RFC11W1R0C, 

RFC11W1P0C, RFC11Y1R0C, 

RFC11Y1P0C, RFC11Z1R0C, 

RFC11Z1P0C

6,500 7 Years

* >>DCC<< The outer bearing race must be removed, discarded and replaced at each major inspection interval (see CHECK section 

of Component Maintenance Manual 61-13-03). It is permissible to use the propeller hub time to track the outer bearing race’s total 

time.

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3. Critical Part Inspections

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.

* Do the inspections for these components as in Component Maintenance Manual 61-13-03. 

The oil transfer tube may be inspected using Maintenance Manual P5189.

** Do the inspections for these components as in Component Maintenance Manual 61-21-05.

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

initial inspection requirement (paragraph 2.(a)) by alternate method of compliance as 

approved by letter from the Manager, FAA Boston Aircraft Certification Office, on June 3, 

1999.

Table AL-2. Propeller Components With Mandatory Inspections

ITEM PART NO. INSPECTION INTERVAL

(FLIGHT HOURS)

Actuator Assembly* 790199-1, -2, -3, -5, -6, -8 Maximum 10,500 hour intervals

Oil Transfer Tube and 

Retainer*

784525-1, -4, -5

814799-1, -4, -5

Initial Inspection*** - within 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)**

782490-2, -16, -27, -38, 

-49, A2, A16, A27, A38, 

A49

Initial Inspection*** - within 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

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4. Ballscrew Spline Inspection

(1) The internal spline of the ballscrew in the PCUs listed in Table AL-3 requires 

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 as in the CHECK section of Chapter 61-22-00 (Propeller Control and 

Adapter).

(2) It is the responsibility of the operator to monitor the flight hours for the PCU.

5. PCU Primary Quill Torque Check

(1) 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 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 as in the CHECK section of Chapter 61-22-00 

(Propeller Control and Adapter).

(2) 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 NO. INSPECTION INTERVAL

(FLIGHT HOURS)

Propeller Control Unit (PCU) 

(Without Quill Damper, and 

Without Secondary Drive Quill)

782490-16, 782490A16, See Airworthiness Directive 

95-22-12.

Propeller Control Unit (PCU) 

(With Quill Damper, and 

Without Secondary Drive Quill)

782490-27, 782490A27 and 

PCUs with the marking 

“SB 14RF-21-61-48” on the 

identification plate

See Airworthiness Directive 

95-22-12.

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

ITEM PART NO. INSPECTION INTERVAL

(FLIGHT HOURS)

Propeller Control Unit (PCU) 782490-38, -49, A38, 

A49

See Airworthiness Directive 

95-22-12.

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6. Hub Retaining Nut Check

A. Do a hub retaining torque check at an interval less than 500 hours in accordance with 

the “A” Inspection Checks, CHECK section, chapter 61-10-00.

7. Special Instructions

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

do the inspection procedures in paragraphs 5, 6, 7 and 8 in Chapter 61-10-00, CHECK, 

in this manual. Complete the appropriate form (Figure 503, Figure 504, or Figure 505) 

and send a copy to the Hamilton Sundstrand address specified on it. 

Feb 20/13