MAINTENANCE MANUAL 14RF-21



# P5189 Page HI-1 TO ALL HOLDERS OF HAMILTON SUNDSTRAND’S MAINTENANCE MANUAL P5189 APPLICABILITY: CN 235 THIS SHEET TRANSMITS REVISI ON 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 c ontact 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 re vision 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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# P5189 MAINTENANCE MANUAL 14RF-21



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# 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 LIMITATION S SECTIONS - FAA APPROVED REMAINDER OF MANUA L - 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 HERE IN 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 MAIN TAIN RECIPIENT’S EQUIPMENT OR AS MAY OTHERWISE BE PERMITTED IN AN APPLICABLE AGR EEMENT 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, MODIFICATION S, SPARE PARTS, DESIGN, OR CONFIGURATION CHANGES, OR TO OBTAIN FAA OR ANY OTHER GOVERNMENT OR REGU LATORY 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 WITHOU T 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 TH E EXPORT OF WHICH IS, OR MAY BE, RESTRICTED BY THE ARMS EXPORT CONTROL ACT AND THE INTERNATIONAL TRAFFIC IN ARMS REGULATIONS (ITAR), 22C.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 ORIGINALLYPROVIDED BY HAMILTON SUNDSTRAND, IS PROHIBITED WITHOUT PRIOR WRITTEN APPROVAL FROM HAMILTON SUNDSTRAND AND AUTHORIZATION UNDER APPLICABLE EXPORT CONTROL LAWS. ITAR/USML: VIII(i)MAINTENANCE MANUAL 14RF-21



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### 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 remain s 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 init ial installation after production. D. Propeller blades and hubs must now be subjected to MI based on published operating time limits for the compon ent 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 t otal 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 accompli shed 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 requir ed 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.



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