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Hartzell Series - Civil Aviation Authority of New Zealand

1. Note 1 Note 2 Requirement Compliance Effective Date For Hartzell propeller models listed in this table any letter or number or lack of a letter or number or any combination of letters or numbers could appear where open parentheses are shown in the model number No further action is required for propeller models listed in this table that have last been serviced repaired or overhauled by a manufacturer approved service center other than Southern California Propeller Service To prevent blade failure that could result in separation of a propeller blades and loss of control of the aircraft disassemble and clean the propeller and inspect per the applicable propeller manufacturer s service documentation for the following Cracks corrosion or pits nicks scratches blade minimum dimensions unapproved localized heating of blade unapproved use of helicoil inserts in actuating pin holes improperly drilled actuating pin holes chemical conversion coat or paint or both applied over corrosion lack of chemical conversion coating lack of paint on internal surfaces bolts incorrectly torqued incorrect parts incorrect installation of parts reinstallation of parts intended for one time use and lack of proper shot peening Repair and replace with serviceable parts as required and reassemble and test per the applicable propeller manufacturer s service documentation FAA AD 2005 14 11 refers Within the next 28 days 25 August
2. rnrnnnnrnnnnrnnnnrnnnnrnnnnrennnrnnnnrnnnnrnnnnrennnrnnrnrensnrnnrnrensnrnnnnnenen 6 Inspection and Shot Peening of Blades rannrnnnnrnnnvrnnnnvnnnvrnnnnrnnnvrnnnnrnnnnrennnrnsreressnnnennne 6 Spring Back up Kit Modification rrronvvnenrnnonvnnenvrrrnvnnenrerrnvnnenrenennnnenrensnvnnenrenennnnennnnenn 7 Blades gt Replacement siisii jasni iadaa aiai enaar eaa Op ai EE etiaai ai 7 Blades Inspection and Shot Peening urnrrrrnrennnvnnrnrnnnnrnnrnronnnvnnrarnnnnnnnsnrennnnnesnrnsnnnnennne 7 Cancelled DCA HARTZ 120B now refers rrrrrvrnanvrnrrvrnnnvrnervrnnnvenervrnnnvnnrrrrnnnvenerrnsnnnnenn 7 Damper Assembly Screws Replacement anrnnnvnnenvnnenvnnenvnnrnvnnenvnnenvnnenvnnrnvnnenrnnenvenenen 7 Hard Alloy Blades Surface CrackS rarrnnnnvnnnnvnnnnvnnenvnnenvenenvnnenvnrenvnnrnvenenrnnenrenenresenvesenen 8 Attachment Bolts Torque Check and Replacement rnranvrnanvnnenvrnnnvnnenvrnnnvrnenvrnnnvnnennne 8 Blade Clamp Assemblies Inspection and Removal from Service c ccceesseeeeeeees 9 Cancelled Purpose fulfilled rrrnnrnnnvrnnnnrnenvrnnnnrnnnvrnnnnnnenvrnnnnnnnnvrernnnnenerensvnnerrressnnnennne 10 Hub Inspection qudtkessdsisdkidaiibidnddskied N E Tana E enai 10 Propeller Hub Inspection and Replacement ursnvnnnnnnvrnenennvnnnrnnvrnnnrnvrnnrerrnnsrrnrrerevnnen 11 Cancelled Purpose fulfilled and DCA HARTZ 146 referS ocoooccccnnocccconoccnconannnnnonnncnnnno 12 Hub and Bla
3. Requirement Compliance Note 1 Note 2 Effective Date b Remove all evidence of defects and remove from service all clamps which exceed rework limitations specified in SI 159B c Magnetic particle inspect and remove from service all cracked clamps d Replace all reworked clamps FAA AD 85 14 10R2 refers By 11 December 1987 unless already accomplished Repeat inspections required per para 2 c at intervals not exceeding 100 hours TIS DCA HARTZ 131 28 February 1986 DCA HARTZ 131A 9 October 1987 Cancelled Purpose fulfilled Hub Inspection Model HC 3Y series propellers with S Ns detailed in Hartzell SB 165DE and installed on aircraft with Lycoming L TIO 540 series engines or installed on agricultural aircraft regardless of engine type These propellers are installed on but not limited to FU24 950 954 PL 12 T 300 PA 31 PA 31 325 PA 31 350 PA 31P 350 and PA 32 R 301T To prevent hub failure due to cracks that originate in the grease fitting holes on the hub which could result in propeller blade separation and loss of the aircraft accomplish the following 1 Perform a combination of visual and eddy current inspection per Hartzell SB 165E Remove propellers with cracked hubs from service before further flight 2 Replace with later style hub post 1983 per SB 165E FAA AD 94 17 13 refers 1 Inspection a For Piper PA 31 325 PA 31 350 aircraft inspect within next 10 hours
4. Inspection and Replacement Models HC B4TN 5 D G J L LT10282 B K 5 3R HC B4TN 5 D G J L LT10282N B K 5 3R and HC B4TN 5 D G J L LT10282NS B K 5 3R propellers installed on Mitsubishi MU 2B 26A 36A 40 60 and any other MU 2 series aircraft To prevent initiation of fatigue cracks in propeller assemblies and possible blade separation accomplish FAA AD 95 01 02 Compliance is required as detailed in FAA AD 95 01 02 30 August 1996 Blade Inspection Model HC B3TN HC B5MP HC E4A and HC D4N series propellers equipped with propeller blades identified by S N in Hartzell ASB HC ASB 61 220 These propellers may be installed on but not limited to Ayres S2R series aircraft To prevent propeller blade separation caused by propeller blade shank cracks emanating from forging flaws accomplish the following Disassemble the propeller and perform a one time fluorescent dye penetrant inspection of a twelve inch long area on both the face and camber sides of propeller blade shanks for forging flaws or cracks per ASB HC ASB 61 220 Remove from service prior to further flight propeller blades exhibiting forging flaws or cracks and replace with serviceable parts FAA AD 96 15 04 refers Propellers installed on agricultural or aerobatic aircraft within next 10 hours TIS For propellers installed on other aircraft within next 60 hours TIS For propellers that have not been inspected per this airworthiness directive and experience a su
5. F before the blade model number Propeller blades with a S N higher than J88010 may have been shot peened at manufacture After several occurrences of pitch change knob fractures Hartzell introduced the shotpeening of pitch change knobs at manufacture from 1 December 2005 refer Hartzell Service Letter No HC SL 61 245 To prevent failure of a blade pitch change knob possibly resulting in loss of aircraft control accomplish the following 1 Inspect rework and shotpeen pitch change knobs per the instructions in Hartzell Alert Service Bulletin ASB No HC ASB 61 263 revision 2 and per the instructions in the blade shank overhaul chapter of Hartzell Aluminum Overhaul Manual No 133C 61 13 33 2 Before fitting a propeller blade ensure the pitch change knob has been shotpeened per requirement 1 of this AD This AD amplifies the shotpeening requirements specified in ASB No HC ASB 61 263 and Hartzell Aluminum Overhaul Manual No 133C 61 13 33 In 2003 Hartzell introduced the shotpeening of the pitch change knobs at every overhaul Shotpeening applies a compressive layer improving the resistance to fatigue which can be compromised by damage in service loads rework or wear NZ Occurrence 07 2080 refers 1 At the next calendar inspection or next 100 hours TIS whichever occurs sooner unless previously accomplished at manufacture or last propeller overhaul whichever is the later and thereafter at every propeller overhaul or w
6. X V series and HA A2V20 1B series propellers with aluminium blades These propellers are installed on but not limited to the following aircraft Twin Commander 500 500A 500S 680F Beech 35 series 35 C33A 58P 95 A55 95 B55 Bellanca 7GCA 7GCB 7GCC Cessna 170 170A 172 175 180 series 182 series 210 series 310 series E310H 320 320 1 320A 320B 402 411 deHavilland DH104 DH114 GAF N22B N24A N22S N22C Grumman G44 G44A Mooney M20 Pacific Aerospace FU 24 FU 24A Pilatus PC 3 PC 6 PC 6 H1 H2 Piper PA E23 250 PA14 PA18 A S 150 PA18A 150 PA22 150 PA22S 150 PA23 series PA24 series PA28 PA28 140 SOCATA GY 80 150 GY 80 160 To prevent blade separation due to cracked blades hubs or blade clamps which could result in loss of control of the aircraft accomplish the following A For hub models HC 1 4 5 8 2 3 X V perform initial and repetitive inspections and if necessary replace with serviceable parts per Hartzell SB HC SB 61 217 Revision 1 as follows 1 Initially perform a fluorescent dye penetrant and eddy current inspection of the blade an optical comparator inspection of the blade retention area a dye penetrant inspection of the blade internal bearing bore and a visual and magnetic particle inspection of the blade clamp and of the hub The initial inspection is required within the following i 1 000 hours time since new TSN for propellers with less than
7. 2001 Issued 28 November 2013 Page 18 of 35 CAA of NZ DCA HARTZ 141A Applicability Note 1 Requirement Note 2 Compliance Effective Date DCA HARTZ 142 Applicability Hartzell Series HC C2YR 4CF Propeller Service Life Reduction Model HC C2YR 4CF propellers with hubs P N D 6522 1 or D 2201 16 and propeller blades P N FC8477A 4 fitted to Sky International Inc Pitts S 2S and S 2B aircraft with Textron Lycoming model AEIO 540 D4A5 engines This AD revised to add note 2 which specifies the relevent manufacturer instructions which pertains to the subject of this AD To prevent fatigue failure of propeller hubs which may result in loss of the aircraft accomplish the following 1 Remove hubs P N D 6522 1 or D 2201 16 and blades P N FC8477A 4 from service before exceeding 2000 flight hours and replace with serviceable hubs and blades before further flight 2 Affected hubs and propeller blades that have accumulated 2000 hours TIS shall not be fitted to any aircraft 3 Affected hubs and propeller blades that have been removed from a Sky International Inc Pitts S 2S or S 2B aircraft shall not be reused on any other aircraft The Pitts S 2S and S 2B propeller blade and hub unit life limits specified in the airworthiness limitations section of Hartzell Propeller Maintenance Manual 113B and the propeller application data for the Aviat Pitts S 2S and S 2B aircraft specified in Hartzell Application Guide 159 pe
8. 2005 Issued 28 November 2013 Page 25 of 35 CAA of NZ DCA HARTZ 150 Applicability Requirement Note 1 Note 2 Compliance Effective Date DCA HARTZ 151 Applicability Requirement Hartzell Series Attachment Bolts Inspection and Replacement All model HC B3TN 2 HC B3TN 3 HC B3TN 5 HC B3MN 3 HC B4TN 3 HC B4TN 5 HC B4MN 5 HC B4MP 3 HC B4MP 5 and HC B5MP 3 propellers installed with propeller mounting bolts P N B 3339 To prevent propeller mounting bolt failures or improperly secured propellers which could lead to separation of the propeller from the aircraft accomplish the following 1 If P N B 3339 bolts from LFC manufacturing Lot No 12 or Lot No 56 are fitted visually inspect and torque check of all eight mounting flange bolts per the instructions in paragraphs 3 A through to 3 B 5 of Hartzell Propeller Inc Alert Service Bulletin No HC ASB 61 279 revision 2 and Alert Service Bulletin Appendix No HC ASBA 61 279 revision 2 If the attachment bolts are not from the affected batch no further action is required If any bolt fails the torque check replace all eight bolts with P N B 3339 bolts that are not from LFC Manufacturing Lot No 12 or Lot No 56 or other equivalent manufacturer approved bolts per ASB HC ASB 61 279 For the location of bolt identification marks refer to figure 1 in ASB HC ASB 61 279 2 Replace all LFC Manufacturing Lot No 12 and Lot No 56 bolts P N B 3339 with bolt
9. A61602B AU11145B A61603B AU11147B A61605B AU11155B A61613B AY520B A61743B AU11175B A61893B D 6529 1 D 6529 1 D 6559 3 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 Hub P N D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6529 1 D 6522 1 D 6522 1 D 6522 1 D 6522 2 D 6522 1 Hartzell Series To prevent in flight propeller blade separation resulting in airframe and engine damage and possible loss of the aircraft accomplish the following For Piper PA 32 series craft with Lycoming 540 series engines rated at 300 horse power or higher Britten Norman BN 2 series aircraft with Lycoming 540 series engines aerobatic aircraft and craft used for agricultural purposes remove affected hubs listed by S N in Table 1 of this AD and replace with serviceable hubs in accordance with paragraphs 3 A through 3 B 3 of ASB HC ASB 61 259 Issued 28 November 2013 Page 20 of 35 CAA of NZ Compliance Effective Date DCA HARTZ 143 Applicability Requirement Compliance Effective Date Hartzell Series 2 For aircraft other than those types listed in paragraph 1 of this AD remove affected hubs listed by S N in Table 1 of this AD and replace with serviceable hubs in accordance with paragraphs 3 A through 3 B 3 of ASB HC ASB 61
10. HA A2MV20 1 Information on modifying the affected propellers may be found in Hartzell SB No s HC SB 61 232 and HC SB 61 233 FAA AD 97 18 02R 1 refers Compliance is required at the times specified within the requirement of this airworthiness directive DCA HARTZ 139 26 September 1997 DCA HARTZ 139A 25 September 2003 BASCO Overhauled Propellers Maintenance Actions Propellers overhauled by Brothers Aero Service Company Inc BASCO USA from November 1996 to October 1998 Propellers affected are Y shank series propellers and those listed by hub S N in FAA airworthiness directive 2001 07 03 To prevent failure of the propellers returned to service by BASCO accomplish the following 1 Disassemble 2 Clean 3 Inspect for the following i Nicks ii Scratches iii Failure of blades to meet minimum dimensions iv Alodine or paint or both applied over corrosion v Lack of chemical conversion coating applied beneath the de ice boots vi Bolts incorrectly torqued vii Incorrect parts viii Incorrect installation of parts and ix Reinstallation of parts intended for one time use aa 4 Repair and replace with serviceable parts as necessary 5 Perform a cold roll operation on the blade shanks 6 Reassemble and test Information on performing an overhaul of the affected propellers may be found in the applicable Hartzell Propeller Overhaul Manual FAA AD 2001 07 03 refers Within next 10 hours TIS 31 May
11. additional letter s which vary the basic propeller hub model designation The airworthiness directive is applicable regardless of whether these letters are present or absent on the propeller hub model designation New or amended ADs are shown with an asterisk Contents Cancelled Purpose Fulfilled ccccccceesssccceeeseeeeeeneeeeeeeneeeeceeeeeeeeeeeeeseaeeesceeeeessneterseaes 4 Split Rings Modification ee eee eee eee eeetee eter eeeeeeeeeeeeeaeeeeaeeseaeeseaeeeeaeeeeaeeeeeeeeeeenieeeeeees 4 Cancelled Purpose Fulfilled iocooiooicnnan ii dialed 4 Cancelled Purpose Fulfilled rrrnrnvrnonvrnnnvvnervrnnnvrnnnvrnnnvnnernrnnnvenernrnsnnnnervrnsnrenesnrnsnnnnenn 4 Cancelled Purpose Fulfilled rrnnnrrronvnnenrnnonvnnenvonenvnnenvonenvnnenvenenvnnenrenenvnnenrenennnnenrenenn 4 Cancelled Purpose Fulfilled ec eecceeesceeeseeteneeeeeeeeaeeseeeeseaeeseaeeseaeeseaeeseaeeseeeseaeeseaeess 4 Cancelled Purpose Fuhe dscns ineeiieo a i 4 Page 1 of 35 CAA of NZ DCA HARTZ 108 DCA HARTZ 109 DCA HARTZ 1 10 DCA HARTZ 112 DCA HARTZ 114B DCA HARTZ 115 DCA HARTZ 116C DCA HARTZ 117A DCA HARTZ 118 DCA HARTZ 119 DCA HARTZ 120B DCA HARTZ 121 DCA HARTZ 122 DCA HARTZ 123A DCA HARTZ 124 DCA HARTZ 126A DCA HARTZ 127 DCA HARTZ 128 DCA HARTZ 129 DCA HARTZ 130A DCA HARTZ 131A DCA HARTZ 132 DCA HARTZ 133D DCA HARTZ 134G DCA HARTZ 135 DCA HARTZ 136 DCA HARTZ 137 DCA HARTZ 138 DCA HARTZ 139A DCA HARTZ 14
12. to April 1968 Requirement Hartzell SB 96 Compliance As detailed Issued 28 November 2013 Page 5 of 35 CAA of NZ Propellers amp Propeller Governors Hartzell Series DCA HARTZ 120B Applicability Requirement Compliance Effective Date DCA HARTZ 121 Effective Date DCA HARTZ 122 Applicability Requirement Compliance Effective Date Blades Inspection amp Shot Peening 1 C8475 type blades with HC E2YK 2B amp HC E2YR 2B propellers 2 7666A Y shank blades with S N below C38994 used on but not limited to HC C2YK 1 HC C2YK 2 8 HC C2YK 4 propellers Those blades only used with HC C2YK 2 G dampered type propellers hub model designation with G suffix letter are excluded 3 All other Y shank blades listed in Hartzell SB 97A To detect blade shank cracks and prevent possible blade failure accomplish the following 1 Applicable to C8475 type blades with HC E2YK 2B amp HC E2YR 2B propeller a Inspect blade shanks and rework as necessary in accordance with Hartzell SB 94A b Inspect blade balance hole and rework in accordance with Hartzell SB 97A 2 Applicable to 7666A Y shank blades with S N below C38994 as detailed in AD Schedule a Inspect blade shanks in accordance with Hartzell SB 97A b Rework or replace blades as necessary in accordance with Hartzell SB 108 3 Applicable to all other Y shank blades listed in Hartzell SB 97A a I
13. years TSO or if the TSO is unknown by 27 April 2007 12 months 27 April 2006 Issued 28 November 2013 Page 27 of 35 CAA of NZ DCA HARTZ 153 Effective Date DCA HARTZ 154 Applicability Note 1 Requirement Note 2 Compliance Hartzell Series Cancelled DCA HARTZ 159 refers 26 November 2009 Propeller Mounting Bolts Torque Inspection Model HC B5MP 3 M10282A 6 and HC B5MP 3 M10876 five bladed propellers The parentheses appearing in the propeller model number indicates the presence or absence of an additional letter s that varies the basic propeller model This AD still applies regardless of whether these letters are present or absent in the propeller model designation To prevent propeller separation due to the possibility of fretting wear occuring between the engine and propeller mounting flanges causing a loss of mounting bolt preload and failure of the bolts accomplish the following 1 If either of the propeller or engine mounting flanges have not been resurfaced per either Hartzell Propeller Inc Alert Service Bulletin SB No A203A dated January 5 1995 or SB No HC SB 61 275 dated June 2 2005 perform a torque inspection of the propeller mounting bolts per the instructions in paragraphs 3 A through 3 A 4 of Hartzell Propeller Inc SB No HC SB 61 275 If the torque of any bolt is found to be less than 90 ft lbs remove and inspect the propeller resurface the flanges
14. 0 60 00 1 Repair or replace as required before further flight per the accomplishment instructions in paragraphs 2 A 3 through to 5 of ASB No 30 60 00 1 FAA AD 2005 18 20 refers Issued 28 November 2013 Page 26 of 35 CAA of NZ Note 1 Note 2 Compliance Effective Date DCA HARTZ 152 Applicability Requirement Note 1 Note 2 Note 3 Note 4 Compliance Effective Date Hartzell Series Certificated maintenance personnel must perform the initial inspection per requirement 1 Thereafter the pilot may perform the repetitive visual inspection per requirement 2 in accordance with CAR Part 43 Appendix A The pilot must be trained and authorised Part 43 Subpart B refers and certification must be provided Part 43 Subpart C refers The replacement of FASTprop propeller de icers with a manufacturer approved propeller de icer per ASB No 30 60 00 1 is a terminating action to this AD 1 Within the next 10 hours TIS 2 Once per day at the first daily preflight inspection 27 October 2005 Propeller Hubs Inspection and Repair Hartzell propeller assemblies with hub model series specified in the following table HC 92W Hub Model Series HC B3R Hub Model Series BHC 92W Hub Model Series HC B3W Hub Model Series HC 92Z Hub Model Series BHC B3W Hub Model Series BHC 92Z Hub Model Series HA B3Z Hub Model Series HC B3P Hub Model Series HC B3Z Hub Model Series These prope
15. 0 DCA HARTZ 141A DCA HARTZ 142 DCA HARTZ 143 DCA HARTZ 144 DCA HARTZ 145 DCA HARTZ 146B DCA HARTZ 147 DCA HARTZ 148 DCA HARTZ 149 DCA HARTZ 150 DCA HARTZ 151 DCA HARTZ 152 DCA HARTZ 153 DCA HARTZ 154 DCA HARTZ 155 DCA HARTZ 156 DCA HARTZ 157 DCA HARTZ 158 DCA HARTZ 159 Cancelled Purpose Fulfilled rrnnvrnonvrnnnvvnvrnrnnnvrnenvrnnnvenervrnsnvenervrnsnnnnervrnsnrnnernrnsnnnnenn 4 Cancelled Purpose Fulfilled rrnnrrnonvnnenrnnonvnnenvrnenvnnenvenenvnnenvenenvnnenrnnenvnnenresennnnenrenenn 4 Cancelled Purpose Fulfilled rrnrnvrnonvrnnnvvnenvrnnnvnnnnvrnnnvenervrnnnvenernrnnnvnnesvrnsnvenervrnsnnnnenn 4 Cancelled Purpose Fulfilled rnnnnrnronrnnnnroronvnnnnrnnennnnnnronenvnnnnrenennnnsnrenenvnnnnresensnnsnretenn 4 Blade Clamps and Blade Bearing Races Inspection ooococinnccnnnccinnccnocccnonccnancnnnnccnancnnnno 5 Hub Spiders INSpectiON oooconcconininicccnnnccnoncccnnnnnancno nana nano nr acc narcn ran nar nc rana r nc rana nc 5 Cancelled DCA HARTZ 139 now FefelS ooooconccincccnoncccnnncnonccnnnncnoncnnnn nn nn ccnnn cana ncnnnn cnn 5 Cancelled Purpose Fulfilled rrnnnrnronnnnnnrononvnnnnrnnennnnnnronennnnnnrnnennnnenrenenvnnsnresennnnsnvesenn 5 Blade and Hub INspectiON ooooccccnnnnccnnnnccnnnnnncnnnna nc 5 EE EEE 5 Blades Inspection amp Shot Peening cocooocccncccnoncccnoccnoncnnnnccnoncnnoncc nan cnnnn cnn nn nnnc cnn cannncnnnns 6 Cancelled Purpose Fulfilled
16. 130 27 May 1983 DCA HARTZ 130A 6 May 2005 Blade Clamp Assemblies Inspection and Removal from Service All model HC X V series propellers with Hartzell P N C 3 blade clamp assemblies with S N prior K6337 To prevent clamp failure 1 Remove from service all clamp assemblies with mismatching S N s on each clamp half or with unreadable S N s 2 Remove from service all clamp assemblies with S N in range 0 through D5293 or inspect as follows a Visually inspect internal inboard radius area of clamps especially next to the clamp bolt hole and remove from service all clamps with signs of corrosion b Magnetic particle inspect all internal and external surfaces of clamp per Hartzell Specification No H S 7 dated 4 August 1981 or approved equivalent and remove from service all clamps with signs of cracks c Dye penetrant inspect all external surfaces of clamp assemblies and remove from service all clamps with signs of cracks 3 Accomplish the following on all blade clamp assemblies with S N s in range D5294 through K6336 per Hartzell SI 159B a Using 10 power magnification visually inspect inner bearing race radius especially next to inner clamp bolt hole for defects such as corrosion tool marks gouges scratches etc Issued 28 November 2013 Page 9 of 35 CAA of NZ Propellers amp Propeller Governors Hartzell Series Compliance Effective Date DCA HARTZ 132 DCA HARTZ 133D Applicability
17. 259 3 Do not install any propeller assembly that has a hub with a P N D 6522 1 D 6522 2 D 6529 1 or D 6559 3 with a S N listed in Table 1 of this AD FAA AD 2003 01 03 refers 1 By 50 hours TSN or by 27 February 2004 whichever occurs first 2 By 100 hours TSN or by 27 February 2004 whichever occurs first 3 After the effective date of this AD 27 February 2003 Anti Ice Boots Removal and Inspection Model HC C2Y K R 1BF F8477 4 propellers with TKS Aircraft De icing Ltd anti ice boots that were installed by Socata Groupe Aerospatiale using TKS Ltd Procedure P232 Specification for the Attachment of Propeller Overshoes These propellers were installed on but may not be limited to Socata TB 20 and TB 21 aircraft To prevent propeller blade separation damage to the aircraft and possible loss of the aircraft do the following 1 For propellers that have been overhauled after the installation of TKS Aircraft De icing Ltd Anti ice boots and have had the anti ice boots re installed using Hartzell Manual 133C ATA 61 13 33 Aluminum Blade Overhaul AS amp T Procedure 4700INS or other approved procedures excluding TKS Procedure P232 no further action is required 2 For propellers that have had the anti ice boots installed using the TKS Procedure P232 but have not had anti ice boots re installed using Hartzell Manual 133C ATA 61 13 33 Aluminum Blade Overhaul AS amp T Procedure 4700INS or other approved pro
18. 3628A DN3630A DN3641A DN3940A DN3944A DN3949A and DN3962A replace the hub with serviceable parts per the instructions in SB No HC SB 61 227 3 Hub Replacement For propellers with suffix A at the end of the S N excluding S N DN3607A DN3609A DN3613A DN3615A DN3628A DN3630A DN3641A DN3940A DN3944A DN3949A and DN3962A replace the hub with serviceable parts per SB No HC SB 61 227 4 Reuse of Affected Propellers Issued 28 November 2013 Page 11 of 35 CAA of NZ Propellers amp Propeller Governors Hartzell Series Note 5 Note 6 Compliance Effective Date DCA HARTZ 135 Effective Date A propeller hub removed from service from an affected aircraft may not be reused on any aircraft The replacement of an affected propeller hub per the instructions in SB No HC SB 61 227 with a Hartzell propeller hub with a suffix letter B at the end of the hub S N is a terminating action to ECI inspection requirements of this AD The inspections and hub replacements mandated by this AD must be accomplished per the instructions in Hartzell Propeller Inc SB No HC SB 61 227 revision 5 dated 28 September 2006 or later FAA approved revisions FAA AD 2001 23 08 refers 1 Within the next 50 hours TIS unless previously accomplished within the last 150 hours TIS and thereafter at intervals not to exceed 150 hours TIS 2 Atthe next overhaul but not to exceed 1000 hours TIS or 72 months whichever occurs sooner aft
19. 50 2 After the effective date of this AD do not install any propeller blade removed in accordance with Hartzell SB HC SB 61 250 on any aircraft FAA AD 2003 04 23 refers Within 200 TIS or before 31 March 2006 31 March 2005 Blade Pilot Tube Bore Inspection All model HC B3TN 5 T10282 propellers installed on Fairchild aircraft models SA226 TC SA226 AT and SA226 T with Garrett TPE331 10UA 511G engines and excluding propellers with blades P N T10282N T10282NB T10282NK or T10282NE Aircraft incorporating STCs SA344GL D SA4872SW and SA345GL D have these engine propeller and aircraft combinations To prevent possible blade failure near the hub which can result in blade separation engine separation damage to the aircraft and possible loss of the aircraft accomplish the following 1 Perform a document search to determine that the propeller blades meet the initial and repetitive compliance requirements of AD 88 24 15 2 Perform a document search to determine that propeller blades P N T10282 have been replaced with P N T10282N T10282NB T10282NK or T10282NE propeller blades 3 Ifthe actions in requirement 1 and 2 have not been done then do one of the following a Inspect the blades per Hartzell SB 136 revision I or b Replace propeller blades with P N T10282N T10282NB T10282NK or T10282NK as applicable 4 If the actions in requirement 1 have been done but not the
20. 900 hours TSN provided that the initial inspections are performed within 60 months TSN or within next 24 months whichever occurs later or ii 100 hours TIS for propellers with 900 or more hours TSN or unknown TSN provided that the initial inspections are performed within 24 months 2 Thereafter perform repetitive fluorescent dye penetrant and eddy current inspection of the blade an optical comparator inspection of the blade retention area and a visual and magnetic particle inspection of the blade clamp The repetitive inspection is required at intervals not to exceed 500 hours TIS or 60 months whichever occurs first since last inspection 3 Thereafter perform a repetitive visual and magnetic particle inspection of the hub This repetitive hub inspection is required at intervals not to exceed 250 hours TIS or 60 months whichever occurs first since last inspection 4 Thereafter perform a repetitive dye penetrant inspection of the blade internal bearing bore This repetitive blade internal bearing bore inspection is required at intervals not to exceed 60 months since last inspection B For hub models HC A D 2 3 X V and HA A2V20 1B except HC A3VF 7 perform initial and repetitive inspections and if necessary replace with serviceable parts per SB HC SB 61 217 as follows Issued 28 November 2013 Page 16 of 35 CAA of NZ Hartzell Series 1 Initially perform a fluorescent dye penetrant and eddy current inspec
21. A 4 August 1995 Cancelled DCA HARTZ 120B now refers Damper Assembly Screws Replacement Models HC C2YK 2CG F F C7666A and HC C2YK 2CLG F F JC7666A with damper assembly C 1576 having S N detailed in Hartzell SB 103 and installed on Piper PA 34 series aircraft Issued 28 November 2013 Page 7 of 35 CAA of NZ Propellers 8 Propeller Governors Hartzell Series Requirement Compliance Effective Date DCA HARTZ 129 Applicability Requirement Compliance Effective Date DCA HARTZ 130A Applicability Requirement Hartzell SB 103 Within the next 100 hours TIS 31 May 1974 Hard Alloy Blades Surface Cracks Hartzell T10173H T10176H T10178H and T10282H hard alloy type blades Hartzell SB 105A FAA AD 74 14 01 refers All blades with less than 1000 hours TIS within the next 50 hours TIS Blades with more than 1000 hours TIS are not affected 18 September 1974 Attachment Bolts Torque Check and Replacement All models HC B3TN 2 HC B3TN 3 HC B3TN 5 HC B4TN 3 HC B4TN 5 HC B4MN 5 and HC B5MP 3 turbo propellers not installed with P N B 3339 bolts and P N A 2048 2 washers To prevent propeller attaching bolt failures or improperly secured propellers which could lead to separation of the propeller from the aircraft accomplish the following 1 On propellers presently installed with P N A 2047 attachment bolts check the torque of all eight propeller attaching bolts with wash
22. Airworthiness Directive Schedule Propellers 8 Propeller Governors Hartzell Series 28 November 2013 Notes 1 DCA HARTZ 101 DCA HARTZ 102 DCA HARTZ 103 DCA HARTZ 104 DCA HARTZ 105 DCA HARTZ 106 DCA HARTZ 107 Issued 28 November 2013 This AD schedule is applicable to Hartzell propellers manufactured under FAA Type Certificate Numbers Propeller Series FAA Type Certificate Number BHC A2 P24EA and P 908 BHC C2 P 920 BHC J2 P37EA HC 82 P 878 HC 92 P16EA and P 892 HC A3 and HC 83 P6EA HC B3 P15EA and P 907 HC B4 P56GL HC B4T P40EA HC C2 P 920 HC 82 P24EA HC C3 P25EA HC C4 P52GL HC D4 and HC E4 P10NE HC E2 P9EA HC E3 P33EA HC F2 P27EA HC F3YR P31EA HC I3 P33EA HC M2 and HC 2M P43GL PHC C3 P25EA PHC G3 P55GL PHC J3 P36EA The FAA is the National Airworthiness Authority NAA responsible for the issue of State of Design Airworthiness Directives ADs for Hartzell propellers State of Design ADs applicable to these propellers can be obtained directly from the FAA web site The link to the FAA web site is available on the CAA web site at http Awww caa govt nz Airworthiness Directives states of design html The date above indicates the amendment date of this schedule Many of the following airworthiness directives contain brackets in the applicability paragraph The brackets that appear in the propeller models indicate the presence or absence of
23. Issued 28 November 2013 Page 22 of 35 CAA of NZ Requirement Compliance Effective Date DCA HARTZ 146B Applicability Note 1 Note 2 Requirement Note 3 Compliance Effective Date Hartzell Series Following an NTSB investigation the FAA determined that T 8 W Propellers were not properly carrying out propeller repairs and overhauls The investigation revealed that overhaul processes had not been carried out rendering the propellers unserviceable To avoid failure of the propeller and loss of control of the aircraft Remove propellers from service and return to an authorised propeller repair centre other than T 8 W Propellers for disassembly and re inspection FAA AD 2003 13 17 refers Within 10 hours TIS 31 August 2003 Blade Pitch Change Knobs Inspection and Rework Model HC Y propellers with Y shank aluminium blades having an F pitch change knob fitted to Textron Lycoming IO 720 series engines installed on FU24 series aircraft This AD revised to mandate the shot peening of pitch change knobs of new or first life blades that have not been shotpeened at manufacture or in accordance with previous revisions of this AD or DCA HARTZ 135 Pitch change knobs shall also be shotpeened at every overhaul or when damage wear or rework exceeds the depth of the pebble grain surface Propellers with aluminium blades having an F pitch change knob can be identified by prefix letter
24. Model HC B4MP 3A propellers fitted to BEECH 1900C aircraft Model HC B4MP 3B propellers fitted to BEECH 300 300LW aircraft Model HC B3TF 7A propellers fitted to BEECH A36 A36TC aircraft Model HC B4MP 3C propellers fitted to BEECH B300 B300C aircraft Model HC B4MN 5AL propellers fitted to CASA C 212 CC and CF aircraft Model HC B3TF 7A propellers fitted to CESSNA 206 aircraft Model HC B3TF 7 propellers fitted to CESSNA 402 aircraft Model HC B3MN 3 propellers fitted to CESSNA 208 208A and 208B aircraft Model HC B3TN 3AEY 3AF propellers fitted to CESSNA 208 208A and 208B aircraft Model HC B3TF 7A propellers fitted to CESSNA P210N aircraft Model HC B3TN 3AEY propellers fitted to DE HAVILLAND CANADA DHC 3 aircraft Model HC B4TN 5NL propellers fitted to DE HAVILLAND CANADA DHC 3 aircraft Model HC B5MA 3M propellers fitted to DE HAVILLAND CANADA DHC 4 aircraft Model HC B4TN 5ML propellers fitted to DORNIER DO228 100 101 200 201 202 and 212 aircraft Model HC B4TN 5L propellers fitted to DORNIER DO228 200 201 202 and 212 aircraft Model HC B5MA 3 J M C propellers fitted to DOUGLAS DC 3C aircraft Model HC B5MA 2 EMBRAER EMB 314 aircraft Model HC B4TN 5EL 5HL 5KL propellers fitted to FAIRCHILD AIRCRAFT SA 226T B aircraft Model HC B3TF 7 7A propellers fitted to FLUG amp FAHRZEUGWERKE AG AS202 32TP aircraft Model HC B3TF 7A propellers fitted to FUJI KM 2D T 5 aircraft Model HC B5MP 5 propellers fitted to GRUMMAN
25. S 2 aircraft Model HC B5MA 5H propellers fitted to GRUMMAN S 2F3AT aircraft Model HC 3BTF 7A propellers fitted to MAULE M 7 420 and MX T 7 420 aircraft Model HC B4TN 5DL 5GL 5JL propellers fitted to MITSUBISHI MU 2B 25A 26A 30 35A 36A 40 MU 2P 60 MU 2N aircraft Model HC B5MP 3 A propellers fitted to NORD 262 FRAKES aircraft Model HC B5MP 3C propellers fitted to NORMAN AEROPLANE NAC 6 65 aircraft Model HC B5MP 3D propellers fitted to POLISH AVIATION MIELEC M 28 and 28B aircraft Model HC B5MP 3G propellers fitted to POLISH AVIATION MIELEC M 28B aircraft Model HC B3TN 5U propellers fitted to PZL MIELEC M18 aircraft Model HC B4TN 5NL propellers fitted to PZL MIELEC M18 aircraft Model HC B5MP 5BL propellers fitted to PZL MIELEC M18 aircraft Model HC B5MP 3C propellers fitted to PZL MIELEC M18 M18A and M18B aircraft Model HC B4MN 5B propellers fitted to ROCKWELL OV 10 LEFT SIDE aircraft Model HC B4MN 5BL propellers fitted to ROCKWELL OV 10 RIGHT SIDE aircraft Model HC B5MP 3A propellers fitted to SHORT BROTHERS SD3 30 aircraft Model HC B5MP 3C propellers fitted to SHORT BROTHERS SD3 60 200 and SD3 SHERPA 200 aircraft Issued 28 November 2013 Page 32 of 35 CAA of NZ Note 1 Requirement Note 2 Note 3 Compliance Effective Date DCA HARTZ 159 Applicability Note 1 Requirement Note 2 Hartzell Series Model HC B3TF 7A propellers fitted to SIAI MARCHETTI AERMACCHI F 260C and D airc
26. TIS and thereafter at intervals not to exceed 10 hours TIS b Agricultural aircraft inspect within next 25 hours TIS and thereafter at intervals not to exceed 25 hours TIS c For all other affected aircraft inspect within next 50 hours TIS and thereafter at intervals not to exceed 50 hours TIS d If any abnormal or unexplained changes occur in propeller vibration or grease leakage inspect prior to further flight 2 Replacement For Piper PA 31 325 PA 31 350 and Agricultural aircraft replace at next overhaul or by 30 June 1995 whichever occurs first Propeller hubs affected by this AD that have been removed from service cannot be returned to service on aircraft types that are not subject to this AD Cumulative fatigue damage may have occurred that is not yet detectable Alternative Rework Performing interim modification per SB 165E allows an operator to extend the inspection period and replacement time of the propeller hub This is considered an alternative means of compliance and a concession is required Applications for a concession should be made on Form MOT 2120 DCA HARTZ 133C 24 August 1993 DCA HARTZ 133D 28 October 1994 Issued 28 November 2013 Page 10 of 35 CAA of NZ Propellers amp Propeller Governors Hartzell Series DCA HARTZ 134G Applicability Note 1 Note 2 Note 3 Note 4 Requirement Propeller Hub Inspection and Replacement Model HC 2Y propeller models also
27. actions in requirement 2 then inspect the blades per Hartzell SB 136 revision I Replace all blades showing evidence of cracks or other unairworthy conditions before further flight Issued 28 November 2013 Page 24 of 35 CAA of NZ Note 2 Compliance Effective Date DCA HARTZ 149 Applicability Hartzell Series After the effective date of this AD compliance is restricted to SB No 136 revision I Installation of propeller blades P N T10282N T10282NB T10282NK or T10282NE as applicable onto a Hartzell Propeller Inc model HC B3TN 5 propeller constitutes terminating action to the inspections repairs and replacements specified in requirements 3 and 4 FAA AD 2005 04 08 refers 1 Within 50 hours TIS 2 Within 50 hours TIS 3 Inspect or replace within 500 hours TSN or TSO or before 31 March 2007 whichever occurs first and thereafter within 500 TIS intervals 4 Within 500 hours since the last Hartzell SB 136 inspection and thereafter within 500 TIS intervals 31 March 2005 Propeller Blades Inspection and Overhaul Hartzell Propellers listed in the following table and which have last been returned to service by Southern California Propeller Service of Inglewood CA Hartzell Propeller Inc HC 2 3 4 HCO 2 3 4 X V MV W Z P R F G L K R 20 30 31 HA HC B 3 4 M P R T A N P HC D E 4 5 A B N P
28. ages 201 to 215 prior to installing a serviceable hub If cracks are found in either the blade or the blade clamps prior to further flight replace with serviceable blade or blade clamps Reassemble the propeller in accordance with Hartzell Propeller Inc Service Manual 118F Revision 2 dated May 1992 pages 57 to 96 for 3 and 4 bladed hub models and Service Manual 132A Revision 2 dated June 1992 pages VII 1 to VII 46 for 5 blade hub models FAA AD 96 18 14 refers Note This AD requires no action for operators with Hartzell propeller models HC B4TN 5 D G J L LT10282 B K 5 3R HC B4TN 5 D G J L LT10282N B K 5 3R and HC B4TN 5 D G J L LT10282NS B K 5 3R installed on Mitsubishi MU 2B 26A 30 36A 40 60 and any other MU 2 Series aircraft which have the referenced propeller models installed These operators must however comply with DCA HARTZ 136 Compliance Replacement March Sept March Sept March Sept is due by end 1997 1997 1998 1998 1999 1999 of Number smseres PG Number S N Series HC B3MN 3 6B TT Er NE AAA AA AG BIN Ez ME Hs se A HC B3TN 4 A Te T A E O HC B3TN 2 AG 159 60 118 119 174 175231 2322388 HC B3TF 7 A CSS T A NO EE E A HC ASVF 7 os pp 1 eza 2139 AN A PA EA O A E CA HC B4MN 5 FL 135 13670 171238 239 406 HC B4MP 3 PW Tt 11631 HC B4MP 4 FUT pp 1148 E po Issued 28 November 2013 Page 14 of 35 CAA of NZ Propellers amp P
29. aries the basic propeller model This AD applies regardless of whether these letters are present or absent in the propeller model designation This AD is applicable to affected propellers regardless whether the propeller has been modified altered or repaired in the area subject to the requirements of this AD For propellers that have been modified altered or repaired so that the accomplishment of the requirements of this AD is affected the owner operator must request approval for an alternative method of compliance The application should include an assessment of the effect of the modification alteration or repair on the unsafe condition addressed by this AD and if the unsafe condition has not been eliminated the request should include specific actions to address it To prevent failure of the propeller hub due to possible cracks which could result in blade separation and loss of aircraft control accomplish the following 1 Eddy Current Inspection Accomplish an Eddy Current Inspection ECI of the propeller hub fillet radius for cracks per Hartzell Propeller Inc SB No HC SB 61 227 revision 5 dated 28 Sep 2006 or later FAA approved revisions If any cracks are found replace the propeller hub before further flight If no cracks are found permanently mark the end of the hub S N with the suffix letter E per the instructions in SB No HC SB 61 227 2 Hub Replacement For propellers with S N DN3607A DN3609A DN3613A DN3615A DN
30. as required and replace all mounting bolts per the instructions in paragraphs 3 B through 3 B 5 of SB No HC SB 61 275 2 If the propeller and engine mounting flanges have been resurfaced per either SB No A203A or SB No HC SB 61 275 and a fretting disk was not installed perform a torque inspection of the propeller mounting bolts per the instructions in paragraphs 3 A through 3 A 4 of Hartzell Propeller Inc SB No HC SB 61 275 If the torque of any bolt is found to be less than 90 ft lbs remove and inspect the propeller resurface the flanges as required and replace all mounting bolts per the instructions in paragraphs 3 B through 3 B 5 of SB No HC SB 61 275 3 If the propeller and engine mounting flanges have been resurfaced per either SB No A203A or SB No HC SB 61 275 and a fretting disk was installed remove the propeller and inspect the propeller and engine mounting flanges Resurface the flanges if necessary and replace the fretting disk Replace all mounting bolts with new mounting bolts Accomplish the inspection and resurfacing per the instructions in paragraphs 3 B through 3 B 5 of SB No HC SB 61 275 FAA AD 2006 22 12 refers Whenever a propeller is removed from an engine for any reason or before being fitted to an aircraft model that is not listed in this AD inspect the propeller and engine mounting flanges and resurface the flanges if required and replace all mounting bolts per the instructions in para
31. cedures excluding TKS Procedure P232 remove anti ice boots inspect and rework anti ice boot areas of propeller blades and install new anti ice boots in accordance with paragraph 3 of the Accomplishment Instructions of Hartzell Propeller Inc ASB HC ASB 61 251 dated April 10 2001 using the compliance schedule as follows FAA AD 2002 06 02 refers Propeller TIS Inspection Fewer than 500 hours TIS and less Within 200 hours TIS but not to exceed 600 than 3 years time since new TSN hours TSN or prior to accumulating 4 years TSN whichever occurs first Greater than 500 hours TIS or 3 Within 100 hours TIS or 1 year from the years or more TSN but less than 6 effective date of this AD whichever occurs years TSN first Six years or more TSN Within 50 hours TIS or within 6 months from the effective date of this AD whichever occurs first 24 April 2003 Issued 28 November 2013 Page 21 of 35 CAA of NZ DCA HARTZ 144 Applicability Requirement Compliance Effective Date Table 1 Hartzell Series Australian Air Props Removal from Service Hartzell 2 bladed Y shank aluminium hub propellers HC 2Y and Hartzell 2 bladed Y shank aluminium hubs last released by Australian Air Props Pty Ltd Building 515 Hartzell Place Bankstown Airport NSW in the period 1 January 1991 through 31 December 1996 and those propellers listed in table 1 Due to incorrect overhaul practices which may l
32. d which if left uncorrected could result in the propeller blade separating from the hub and cause loss of aircraft control accomplish the following Determine if the propeller has been serviced repaired or overhauled by Oxford Aviation Limited trading as CSE Aviation before November 2003 If not no further action is required If the propeller has been serviced repaired or overhauled by Oxford Aviation Limited trading as CSE Aviation before November 2003 contact the Aircraft Certification Unit for further instruction at Civil Aviation Authority P O Box 31 441 LOWER HUTT Attention Team Leader Continuing Airworthiness FAA AD 2006 24 07 refers If the propeller has been overhauled by another approved propeller repair facility after October 2003 no further action is required A copy of FAA AD 2006 24 07 is may be obtained from http www airweb faa gov Regulatory and Guidance Library Within the next 50 hours TIS or by 21 February 2007 whichever is the sooner 21 December 2006 Propeller Blade Shank Inspection and Rework Model JHC OOYO OOO compact series constant speed or feathering propellers fitted with Hartzell manufactured Y shank aluminum blades These propellers are installed on but not limited to Aermacchi S pA formerly Siai Marchetti S 208 aircraft Aero Commander 200B and 200D aircraft Aerostar 600 aircraft Beech 24 35 36 45 55 56TC 58 60 and 95 aircraft Bellanca 14 and 17 series aircra
33. dden or unusual vibration inspect prior to further flight 30 August 1996 Hub Replacement Models HC A3VF 7 HC B3TF 7 HC B3MN 3 HC B3TN 2 HC B3TN 3 HC B3TN 5 HC B4MN 5 HC B4MP 3 HC B4TN 3 HC B4TN 5 HC B5MA 3 HC B5MP 3 HC B5MP 5 HC B3MN 5 HC B3TN 4 HC B4MP 4 and HC B5MN 3 propellers These propellers may be installed on but not limited to the following aircraft ASTA N22B N24A Ayres Corporation S 2R Beech A36 65 90 65 90A C90 Cessna 208 208A 421 402 P210N de Havilland DH 114 DHC 2 DHC 6 Embraer EMB 110P1 EMB 110P2 Mitsubishi MU 2B series Pacific Aerospace 08 600 Pilatus PC 6 A H2 B1 H2 B H2 B2 H2 B2 H4 PC 7 Piper PA31 T1 T2 T3 PA31P Schweizer Grumman G 164A G 164B and Twin Commander 690A 690B 690C 695 695A To prevent propeller hub blade or blade clamp failure accomplish the following 1 Disassemble the propeller in accordance with Hartzell Propeller Inc Service Manual 118F Revision 2 dated May 1992 pages 15 to 19 for 3 and 4 bladed hub models and Service Manual 132A Revision 2 dated June 1992 pages IV 5 to IV 11 for 5 bladed hub models Remove the hub from service and replace the hub with a serviceable hub per the compliance schedule in Table 1 of this AD Issued 28 November 2013 Page 13 of 35 CAA of NZ Propellers amp Propeller Governors Hartzell Series Utilise Table 1 of this AD in accordance with the follow
34. de Inspection and Replacement ooooconoccccnncoccnononcnonononcnnnnnanononan cnn nano ncnnnnos 13 Blade INSPECHON ici EE 13 hub Replacement eirinn a A a 13 Blades Rework and Inspection oooooccccononcconancncnononcncnnnoncnnnanononnnonnnnnnnen nr n nan cnn nnen cre nnnnns 16 BASCO Overhauled Propellers Maintenance Actions oooconoccccnnocccconccncnononncononancnnnnnos 18 HC C2YR 4CF Propeller Service Life Reduction uanrnranrnnnnrnnonrnnnnrnnenrnnnnrnnenrnnnnrenen 19 Two Bladed Aluminium Hubs Replacement rrnnrnnnvnvnnnnnnnvrnnnnnvrnererevnnnrrnerernrnnrnerernrnnn 19 Anti Ice Boots Removal and Inspection oooooccccnnocccononcccnononcncnnnon cnn norn no nnnn nro rnnrncn cnn 21 Australian Air Props Removal from Service srrrorvrnnnvrnrnvrnnnvrnrrvrnnnvrrrrvrnnnvrnrrvrnnnvnnennn 22 T 8 W Propellers Inc Overhaul rernnrnnenvnnonvnnnnvnnenvnnenvnnenvnnenvnnenvnnenvnnenvenenvenenrnnenvesennn 22 Blade Pitch Change Knobs Inspection and Rework urnrnrnnrnnnvrnnnnrnnnvrnnnnrnerrrernnnnennnn 23 Propeller Blades Replacement rrnnnnnnvnrnrnnvvnrnnnvennnnnnvnnnrnnvnnnnnnvnennvnnnennsnnennnvnnvnenennnn 24 Blade Pilot Tube Bore Inspection rsnnrrnrennvrnnrvnvrnnnvnvrnerernrnnnrrnrrennrnnrnererrnnsrrnererernnen 24 Propeller Blades Inspection and Overhaul uasrrranvnnnnvnnonvnnenrnrenrnnnnrenenrnnnnrnnenrnsenrene 25 Attachment Bolts Inspection and Replacement ooconnccccnnonccc
35. e inspection method Particular attention should be paid to the inside surface of the clamps around the nipple tappings and bolt locations 2 Remove blade bearing and inspect for serviceability Crack check inner and outer bearing races 3 Replace any clamp or bearing found defective before further flight Compliance Agricultural aircraft at intervals not exceeding half overhaul life except that propellers installed on Aerocommander B1 Intermountain Callair aircraft shall be inspected at intervals not exceeding 500 hours TIS Non agricultural aircraft at intervals not exceeding half overhaul life for propellers with clamps having 4000 or more hours TIS or where TTIS is unknown Effective Date DCA HARTZ 114A 31 October 1973 DCA HARTZ 1 148 14 April 1978 DCA HARTZ 115 Hub Spiders Inspection Applicability HC 12X20 1 2 3 5 7B Requirement Hub spiders are to be replaced in accordance with Hartzell SB 32 amended 11 August 1964 FAA AD 64 28 1 also refers Compliance Within the next 100 hours TIS and thereafter every 25 hours TIS DCA HARTZ 116C Cancelled DCA HARTZ 139 now refers DCA HARTZ 117A Cancelled Purpose Fulfilled DCA HARTZ 118 Blade and Hub Inspection Applicability HC 92ZF 8847 when fitted to agricultural aircraft Requirement Hartzell SB 78 Compliance Every 500 hours TIS for propellers with over 1000 hours TIS DCA HARTZ 119 Blade Inspection Applicability Blades of design 7633 4 built prior
36. ead to failure of the propeller hub and loss of control of the aircraft remove from service 1 Any Hartzell HC 2Y propeller incorporating a hub last released by Australian Air Props PTY Ltd following a propeller strike in the period 1 January 1991 through 31 December 1996 and 2 Propeller Hubs listed in table 1 of this directive For propellers removed IAW with requirement 1 dismantle the propeller and inspect the hub preload plate shelf area for evidence of a machining repair Remove from service any propeller hub found to have machining of the preload plate shelf contrary to Hartzell Standard Practices Manual 202A For propellers listed in table 1 of this directive remove hub from service and scrap IAW the manufacturer s procedures Report any propellers removed from service IAW the requirements of this AD to Team Leader Continuing Airworthiness Aircraft Certification Unit CAA CASA AD AD PHZL 77 refers Within 50 Hours TIS or 31 October 2003 whichever occurs first 31 August 2003 Model Serial Number HC F2YL 4 1801 S HC E2YL 2 BG2664 HC E2YL 2 BG2721 HC E2YL 2 DP3940 HC E2YL 2 BG3628 HC M2YR 1 EN359 HC M2YR 4 BBB HC M2YR 1 FB394 HC C2YF 2 AM3316 HC C2YF 2 AM3088 DCA HARTZ 145 T amp W Propellers Inc Overhaul Applicability All Hartzell Propellers that were overhauled by T amp W Propellers Inc of Chino California and are listed in Table 1 of FAA AD 2003 13 17
37. een 2 000 and 2 350 rpm and above 2 600 rpm in acrobatic flight These propellers are installed on but are not limited to Mooney M20E and M20F aircraft Piper PA 28R 200 aircraft and Pitts S 1T and S 2A aircraft 3 For model HC C2YK 000 0084750 0 or 8477 propellers that have not been inspected and reworked in accordance with FAA AD 74 15 02 remove the propeller and modify the pitch change mechanism and replace the blades with equivalent model blades prefixed with a letter F per Hartzell Service Letter No 69 and Hartzell SB No 101D Inspect and repair or replace blades per the instructions in Hartzell SB No 118A FAA AD 2007 26 09 refers 1 2 8 3 By 31 March 2008 28 February 2008 Issued 28 November 2013 Page 30 of 35 CAA of NZ DCA HARTZ 157 Applicability Note 1 Requirement Note 2 Compliance Effective Date DCA HARTZ 158 Applicability Hartzell Series Propeller Hubs Inspection and Replacement Lefthand rotating model HC 2 3 Y K R 2 two and three bladed aluminum hub compact series propellers with hubs having a non suffix S N and lubrication holes located on the shoulder of the hub blade socket These propellers are known to be installed on Lycoming LIO 360 series and LO 360 series engines fitted to Piper Seneca PA 34 200 aircraft and Seminole PA 44 180 aircraft and Hawker Beechcraft model 76 Duchess aircraft The parentheses appearing in the propeller model numbe
38. eight P N B 3339 attaching bolts and remainder of bolt if desired and to the flat surfaces of the eight P N A 2048 2 washers or other equivalent manufacturer approved serviceable bolts and washers and install the attaching bolts and flat washers through the engine flange and into the propeller flange Issued 28 November 2013 Page 8 of 35 CAA of NZ Propellers amp Propeller Governors Hartzell Series Note 1 Note 2 Compliance Effective Date DCA HARTZ 131A Applicability Requirement d Torque all attaching bolts with a torque wrench and an appropriate adapter to 40 ft los and then to 80 ft lbs following sequence A shown below Final torque all attaching bolts using sequence B shown below to 100 ft lbs to 105 ft lbs Safety wire lock all attaching bolts in a manufacturer approved manner oe Cie AROS y 6 14 8 2 Oa DO 3 2 SY ZAS A B A bolt with P N A 2047 has the letter H stamped inside a triangle on the bolt A bolt with P N B 3339 has the P N stamped inside the cupped head The replacement of propeller attachment bolts and washers with P N B 3339 bolts and P N A 2048 2 washers or other equivalent manufacturer approved serviceable bolts and washers per Hartzell Owner s Manual 139 61 00 39 and Hartzell service instruction 140A revision 9 is a terminating action to this AD FAA AD 83 08 01 R2 refers 1 Within 300 hours TIS 2 With every propeller replacement DCA HARTZ
39. er 20 December 2001 the effective date of DCA HARTZ 134D 3 Propeller hubs installed on any aircraft that have been used for agricultural operations At next overhaul but not to exceed 2000 hours TIS or 36 months whichever occurs sooner after 20 December 2001 the effective date of DCA HARTZ 134D Propeller hubs installed on aircraft certificated in the acrobatic category At next overhaul but not to exceed 1000 hours TIS or 72 months whichever occurs sooner after 20 December 2001 the effective date of DCA HARTZ 134D Propeller hubs installed on Piper PA 32 series aircraft with Textron Lycoming 540 series engines that are rated at 300 HP or higher or installed on Pilatus Britten Norman or Britten Norman BN 2 series aircraft also known as Islander or Trislander with Textron Lycoming 540 series engines At next overhaul but not to exceed 2000 hours TIS or 72 months whichever occurs sooner after 20 December 2001 the effective date of DCA HARTZ 134D 4 From 23 December 2010 DCA HARTZ 134F 1 June 2006 DCA HARTZ 134G 23 December 2010 Cancelled Purpose fulfilled and DCA HARTZ 146 refers 29 November 2007 Issued 28 November 2013 Page 12 of 35 CAA of NZ Propellers amp Propeller Governors Hartzell Series DCA HARTZ 136 Applicability Requirement Compliance Effective Date DCA HARTZ 137 Applicability Requirement Compliance Effective Date DCA HARTZ 138 Applicability Requirement Hub and Blade
40. ers installed with a torque wrench and an appropriate adapter The torque should be 100 ft lbs to 125 ft Ibs with dry threads Do not use any lubricant with the P N A 2047 bolts If the torque of each P N A 2047 bolt is within the 100 ft lbs to 125 ft lbs torque range safety wire lock all attaching bolts in a manner approved by the manufacturer At next propeller disassembly remove all eight bolts and washers and replace with P N B 3339 bolts and P N A 2048 2 washers or other equivalent manufacturer approved serviceable bolts and washers per requirement 2 of this AD If the torque of any one of the bolts is found to be less than 100 ft Ibs remove all eight bolts and washers and replace with P N B 3339 bolts and P N A 2048 2 washers or other equivalent manufacturer approved bolts and washers per requirement 2 of this AD 2 Install all new propellers and serviceable propellers with P N B 3339 bolts and P N A 2048 2 washers or other equivalent manufacturer approved serviceable bolts and washers per Hartzell Owner s Manual 139 61 00 39 and Hartzell service instruction 140A revision 9 taking note of the following a Install the propeller oil seal to the engine flange after ensuring that the engine and propeller flanges are clean b Carefully install propeller on the engine flange ensuring that complete and true contact is established c Apply MIL T 83483 Petrolated Graphite or Hartzell Lubricant P N A 3338 to threads of the
41. ft Cessna 182 and 188 aircraft Embraer EMB 200A aircraft Maule M5 aircraft Mooney M20 and M22 aircraft Pilatus Britten Norman or Britten Norman BN 2 BN 2A and BN 2A 6 aircraft Piper PA 23 PA 24 PA 28 PA 30 PA 31 PA 32 PA 34 PA 36 and PA 39 aircraft Pitts S 1T and S 2A aircraft and Rockwell 112 114 200 500 and 685 series aircraft Issued 28 November 2013 Page 29 of 35 CAA of NZ Note 1 Note 2 Note 3 Requirement Note 4 Note 5 Compliance Effective Date Hartzell Series The parentheses appearing in the propeller model number indicates the presence or absence of an additional letter s that varies the basic propeller model This AD applies regardless of whether these letters are present or absent in the propeller model designation Propellers are considered in compliance with the inspection and rework requirements of this AD if all the blades have a S N D47534 onwards or if all the blades are identified with the letters PR or R which is ink stamped on the camber side or if the letters RD are metal stamped on the blade butt This AD supersedes FAA AD 2002 09 08 and no further action is required for propellers in compliance with FAA AD 77 12 06R2 To prevent failure of the propeller blade due to the possibility of fatigue cracks in the aluminium blade shank radius which could result in damage to the aircraft and loss of aircraft control accomplish the following 1 For model JHC 0 Y c
42. graphs 3 B through 3 B 5 of SB No HC SB 61 275 1 For propellers with 3000 or more hours TSN If the bolt torque inspection has never been done accomplish a propeller mounting bolts torque inspection before further flight or Within 120 hours TIS since last inspected per FAA AD 2004 21 01 or within the next 120 hours TIS whichever occurs sooner unless already accomplished and Thereafter at intervals not to exceed 120 hours TIS Issued 28 November 2013 Page 28 of 35 CAA of NZ Effective Date DCA HARTZ 155 Applicability Note 1 Requirement Note 2 Note 3 Compliance Effective Date DCA HARTZ 156 Applicability Hartzell Series For propellers with less than 3000 hours TSN Within 3000 hours TSN and thereafter at intervals not to exceed 120 hours TIS 2 Within the next 120 hours TIS for flanges that were resurfaced 1500 hours ago and thereafter at intervals not to exceed 120 hours TIS 3 Within the next 120 hours TIS for flanges that were resurfaced 1500 hours ago and thereafter at intervals not to exceed 1500 hours TIS 30 November 2006 Propeller Maintenance Inspection and Rework Hartzell propellers which have been serviced by Oxford Aviation Limited in the United Kingdom trading as CSE Aviation before November 2003 For a list of affected propeller P Ns and S Ns refer to table 1 in FAA AD 2006 24 07 To detect and correct inspections and repairs that might not have been accomplished an
43. hen the damage wear or rework on the pitch change knob exceeds the depth of the pebble grain surface 2 From 29 November 2007 DCA HARTZ 146 25 September 2003 DCA HARTZ 146A 25 September 2003 DCA HARTZ 146B 29 November 2007 Issued 28 November 2013 Page 23 of 35 CAA of NZ DCA HARTZ 147 Applicability Note 1 Note 2 Requirement Compliance Effective Date DCA HARTZ 148 Applicability Note 1 Requirement Hartzell Series Propeller Blades Replacement Model HC B3TN 5 propellers with part numbers P N s T10176H B 5 T10176H K 5 T10176H 5 T10178H 11 T10178H 11R T10178H B 11 and T10178H B 11R blades that are installed on Mitsubishi MU 2 aircraft These blades may be fitted to other aircraft types including Rockwell 690A and Cessna 441 however the propeller state of design authority advises failures to date have been limited to the MU 2 Compliance with the SB is recommended for other aircraft types The parentheses indicate the presence or absence of an additional letter s which vary the basic propeller blade model designation This AD still applies regardless of whether these letters are present or absent on the propeller blade model designation 1 To prevent propeller blade separation damage to the aircraft and possible loss of the aircraft remove and replace propeller blades in accordance with paragraphs 3 A through 3 C 3 of the Accomplishment Instructions in Hartzell SB HC SB 61 2
44. ing example Model HC B3TN 3 series propellers starting with S N BU1 through BU377 require replacement before the end of March of calendar year 1997 S N BU378 through BU754 require hub replacement before the end of September of 1997 and so forth The affected hubs can only be replaced with serviceable hubs having a S N not listed in Table 1 of this AD for that propeller model or serviceable hubs having a S N for which replacement is not yet required in accordance with Table 1 of this AD Some existing propeller hub S Ns include a suffix letter such as an A The presence or absence of this letter has no significance in determining compliance Since a hub may be used in various propeller models the S N and the model number shown in Table 1 of this AD may not coincide Precedence is given to the hub S N in determining compliance requirements The hub model is only given as a reference Hub replacement must be accomplished by the end of the calendar month indicated at the top of the appropriate column in Table 1 of this AD The S N ranges in this table identify the propeller hubs that require replacement by the end of that month 2 Perform a fluorescent penetrant inspection of blades for cracks in accordance with Hartzell Propeller Inc SB 136H dated March 12 1993 prior to installing a serviceable hub Perform magnetic particle inspection of blade clamps for cracks in accordance with Hartzell Service Manual 202A dated March 1993 p
45. known as Y shank propellers installed on Piper PA 32 series aircraft with Textron Lycoming 540 series engines that are rated at 300 HP or higher Model HC 2Y propeller models also known as Y shank propellers installed on Pilatus Britten Norman or Britten Norman BN 2 series aircraft also known as Islander or Trislander with Textron Lycoming 540 series engines Model HC 2Y propeller models also known as Y shank propellers installed on any aircraft certificated in the aerobatic category or used for aerobatics Model HC 2Y propeller models also known as Y shank propellers installed on any aircraft that have been or are used for agricultural operations For reference the aircraft and propellers listed in table 2 of Hartzell Propeller Inc SB No HC SB 61 227 revision 5 are affected by this AD For aircraft not listed in table 2 of the SB review the AD applicability to determine if the propeller hub fitted to the aircraft is affected This AD revised to clarify the compliance and the requirements This AD does not apply to Hartzell HC 2Y propeller models with the suffix letter B at the end of the hub S N Affected propellers have model numbers in the form of HC 2Y which have no suffix letter or have the suffix letter A or E at the end of the hub S N The parentheses appearing in the propeller model number indicates the presence or absence of an additional letter s that v
46. llers assemblies are installed on but not limited to Beech 18 and 35 series aircraft Cessna 172 175 175A 190 195 195A 195B 421 and 421A aircraft Pacific Aerospace Fletcher FU 24 and FU 24A aircraft and Piper PA 23 PA 24 and PA 25 aircraft To detect corrosion and mechanical damage that can cause failure of a propeller which could result in loss of control of the aircraft inspect and rework the propeller blade bore and balance hole per the accomplishment instructions in paragraph 3 A of Hartzell Service Bulletin No HC SB 61 136 revision I and the applicable Hartzell Blade Overhaul Manual FAA AD 2005 18 12 refers Refer to the applicable Hartzell maintenance manuals for information on inspecting the propeller components for cracks corrosion or pits nicks scratches wear blade minimum dimensions and damage in the blade balance bore Actions accomplished per Hartzell Service Bulletin No HC SB 61 136 revision G or H are acceptable Propellers are to be inspected per Advisory Circular AC43 5A and CAR Part 43 Appendix C every 4 years Propellers are to be overhauled at the TBO recommended by the manufacturer in terms of operating hours per Advisory Circular AC43 5A For propellers with more than 10 years TSO by 27 October 2008 36 months For propellers with more than 15 years TSO by 27 April 2008 24 months For propellers with more than 20 years TSO by 27 October 2007 18 months For propellers with more than 25
47. n in paragraph 2 A of SB No HC SB 61 269 Hartzell SB No HC SB 61 227 revision 2 dated 18 April 2005 and AD DCA HARTZ 134F FAA AD 2001 23 08 refers pertains to the subject of this AD FAA AD 2009 22 03 refers Within the next 50 hours TIS unless previously accomplished and thereafter at intervals not to exceed 100 hours TIS 26 November 2009 Issued 28 November 2013 Page 34 of 35 CAA of NZ Hartzell Series http www caa govt nz Airworthiness Directives states of design html 72 08 04 T10173 and T10176 Blades Inspection and Replacement DCA HARTZ 122 refers Effective Date 11 April 1972 87 15 05R1 Propeller Blades Inspection and Replacement Effective Date 2 December 1987 94 03 11 Propeller Hub Arm Assemblies Inspection and Replacement Effective Date 28 February 1994 95 03 03 Propeller Hub Arm Bore Inspection and Replacement Effective Date 17 March 1995 2013 15 04 Hydraulic Bladder Diaphragm Effective Date 30 August 2013 Issued 28 November 2013 Page 35 of 35 CAA of NZ
48. n topdressing operations must be fitted with A 969 split rings before further flight 4 Normal category aircraft may have split rings P N A 159 N but rings P N A 969 are strongly recommended 5 All split rings shall be replaced at each overhaul 6 In the case of propellers fitted to FU 24 O 470 N aircraft split ring replacement must be accomplished in accordance with the provisions of NZCAR Part III Leaflet B 28 3 7 Check that saw cuts of split rings are located on each side of the spider arm or in plane of rotation during assembly of propellers incorporating such rings All work to be carried out in approved propeller overhaul shops At overhaul Cancelled Purpose Fulfilled Cancelled Purpose Fulfilled Cancelled Purpose Fulfilled Cancelled Purpose Fulfilled Cancelled Purpose Fulfilled Cancelled Purpose Fulfilled Cancelled Purpose Fulfilled Cancelled Purpose Fulfilled Cancelled Purpose Fulfilled Issued 28 November 2013 Page 4 of 35 CAA of NZ Propellers amp Propeller Governors Hartzell Series DCA HARTZ 114B Blade Clamps and Blade Bearing Races Inspection Experience with propellers using blade clamps has shown that in addition to periodic blade clamp inspections a part overhaul life inspection of bearing races for circumferential cracks is necessary Applicability All models with clamps on piston engine installations Requirement 1 Remove and crack check blade clamps using magnetic particl
49. nanoncnononcncnononcnc nano ncnnno nono 26 Goodrich FASTprop De icers Inspection and Replacement ooocncccnnnccnnnccnonccnnnccnannn 26 Propeller Hubs Inspection and Repair oooocccnnnccccnnoncncnnnoncnnnononononon cnn nano cnn crono nn nnnnnnnnnnnnss 27 Cancelled DCA HARTZ 159 refers cooooicincccnnniccncccnonnnnnnncnnnn non ccnnr crac cnn rca 28 Propeller Mounting Bolts Torque INnSpecti0N ooooccccnnnnccononcccnononcncnnnancn crono nonnnancnnnnnos 28 Propeller Maintenance Inspection and Rework rerrrnnrnerenvrnnnrnnvrernrnvrnererrennrenvrenerenen 29 Propeller Blade Shank Inspection and Rework rarrnnanrnnanvnnnnvnnonrnnrnrnnenrnnenrnnsnrnsenrene 29 Propeller Hubs Inspection and Replacement rerrrnnvnnnvrvvvnnnnnvrnrnrnvrnnrrrnrennennnrerrrnnnne 31 Counterweight Slug Attach Bolts Inspection and Replacement urnrnnnnrnnnnrnnnnvnnnnrnn 31 Propellers Hubs Inspection and Replacement enrnnnvrnnnvnvvnnnvnvvnnnnnnvnnrrrnrrnnrrnrensennnnn 33 http www caa govt nz Airworthiness Directives states of design htmi Issued 28 November 2013 Page 2 of 35 CAA of NZ 72 08 04 T10173 and T10176 Blades Inspection and Replacement rrnnnnnvrnnnnnvrnnnvvvrnnnnn 35 87 15 05R1 Propeller Blades Inspection and Replacement mnnsnnrnnnvnnvnnnrnnvrnnnrnvrnererrnnnrrnrrerrrnnnn 35 94 03 11 Propeller Hub Arm Assemblies Inspection and Replacement rrrnnnrnnvvnnrnnnrnnvr
50. nnrrnnnr 35 95 03 03 Propeller Hub Arm Bore Inspection and Replacement rrnnnrnnvrnnnvnvrnnnvrvrnnnrvnrrerrrnnnn 35 2013 15 04 Hydraulic Bladder Diaphragm eerenvrnnnnnnvrnnrrnvnnnrenvrnnnennvnnnrrvvnnnnenvrersrnnrnerersrennenneresrrnenne 35 Issued 28 November 2013 Page 3 of 35 CAA of NZ Propellers amp Propeller Governors Hartzell Series DCA HARTZ 101 DCA HARTZ 102 Applicability Requirement Note Compliance DCA HARTZ 103 DCA HARTZ 104 DCA HARTZ 105 DCA HARTZ 106 DCA HARTZ 107 DCA HARTZ 108 DCA HARTZ 109 DCA HARTZ 110 DCA HARTZ 112 Cancelled Purpose Fulfilled Split Rings Modification HC 82X20 1B all except HC 2AX series To eliminate the possibility of split ring failures the following action must be taken 1 All split rings P N A 159 including spares stocks are to be withdrawn from service and mutilated to prevent further use not later than the completion of 50 hours TIS commencing 21 November 1958 2 All topdressing aircraft shall be fitted with split rings P N A 969 This will involve modification to the bearing according to Hartzell instructions and the addition of the numeral 1 after dash number of propeller In the case of propellers on topdressing aircraft using engines of 225 hp or less with split rings P N A 159 N already fitted these rings may continue in service until next overhaul when split rings P N A 969 shall be fitted 3 Propellers fitted to engines exceeding 225 hp o
51. nspect and rework as necessary in accordance with Hartzell SBs 94A and 97A FAA ADs 73 10 03 and 75 07 05 refer 1 At intervals not exceeding 1000 hours TIS 2 Within the next 100 hours TIS unless already accomplished and thereafter at intervals not exceeding 1000 hours TIS 3 At each overhaul 1 May 1975 Cancelled Purpose Fulfilled 23 February 2012 Inspection and Shot Peening of Blades Propellers and blades fitted to United Aircraft of Canada PT6A Airesearch TPE 331 and Allison 250 B engines as detailed in the FAA directive FAA AD 72 08 04 As detailed in FAA AD 72 08 04 11 April 1972 Issued 28 November 2013 Page 6 of 35 CAA of NZ Propellers amp Propeller Governors Hartzell Series DCA HARTZ 123A Applicability Requirement Compliance Effective Date DCA HARTZ 124 Applicability Requirement Compliance Effective Date DCA HARTZ 126A Applicability Requirement Compliance Effective Date DCA HARTZ 127 DCA HARTZ 128 Applicability Spring Back up Kit Modification Models HC E2YK 2RB HC E2YR 2RB and HC E2YL 2 propellers equipped with 8465 7R 7663 4 or J7663 4 non counterweighted type blades Hartzell SL 62 FAA AD 71 21 9 refers At overhaul DCA HARTZ 123 31 August 1972 DCA HARTZ 123A 31 March 1978 Blades Replacement All HC C3YR 1 8475R propellers installed on Lycoming IO 720 series engines and all other Y shank model 8475 and 8477 non counterweigh
52. of the blade an optical comparator inspection of the blade retention area a visual and magnetic particle inspection of the blade clamp and a dye penetrant inspection of the blade internal bearing bore The initial inspection is required within the following i 3 000 hours TSN for propellers that have never been overhauled and have less than 2 500 hours TSN on the effective date of this AD provided that the initial inspections are performed within 60 months TSN or within next 24 months whichever calendar time occurs later or ii 3 000 hours TIS since last overhaul for propellers that have been overhauled but have less than 2 500 hours TIS since last overhaul provided that the initial inspections are performed within 60 months TIS since last overhaul or within next 24 months whichever calendar time occurs later or iii 500 hours TIS for propellers that have never been overhauled and have 2 500 or more hours TSN or propellers which have been overhauled and have 2 500 or more hours TIS since last overhaul or propellers with unknown TSN provided that the initial inspections are performed within next 24 months 2 Thereafter perform repetitive fluorescent dye penetrant and eddy current inspection of the blade an optical comparator inspection of the blade retention area and a visual and magnetic particle inspection of the blade clamp The repetitive inspection is required at intervals not to exceed 3000 hours TIS or 60 months whicheve
53. ompact series Y shank propellers that have not been inspected and reworked in accordance with FAA AD 77 12 06R2 remove and inspect blades per the instructions in Hartzell Service Bulletin SB No 118A Rework or replace blades as required before further flight Hartzell SB No 118A requires the cold rolling of the propeller blade shank Cold rolling is a critical requirement in the prevention of cracks in the blade Any rework in the blade shank area will necessitate the cold rolling of the blade shank area apart from the one time cold rolling requirement of this AD 2 Instrument panel modifications on aircraft fitted with propeller models JHC C2YK 7666A installed on undampened 200 hp or more Lycoming lO 360 series engines that have not been modified per FAA AD 77 12 06R2 For standard category aircraft re mark the engine tachometer face or bezel with a red arc restricting the engine speed range between 2 000 and 2 350 rpm and remove the present vibration placard and affix a new placard near the engine tachometer that states Avoid continuous operation between 2 000 and 2 350 rpm For acrobatic aircraft re mark the engine tachometer face or bezel with a red arc restricting the engine speed range i e between 2 000 and 2 350 rpm and also between 2 600 and 2 700 rpm red line and remove the present vibration placard and affix a new placard near the engine tachometer that states Avoid continuous operation betw
54. or 12 months whichever occurs sooner 2 From 31 July 2008 31 July 2008 Counterweight Slug Attach Bolts Inspection and Replacement The following steel hub turbine propeller models fitted with propeller blade counterweight slug bolts P N B 3386 14H from LFC manufacturing lot 224 Model HC B3TN 5K propellers fitted to AERO COMMANDER 680T 680V and 681 aircraft Model HC B3TN 5DL 5FL 5NL propellers fitted to AERO COMMANDER 690 A B C and 695A aircraft Model HC A3MVF 7B propellers fitted to AEROSPACE TECHNOLOGIES N22B N24A N22S and N22C aircraft Model HC A3VF 7 7B propellers fitted to AEROSPACE TECHNOLOGIES N22B N24A N22S and N22C aircraft Model HC B5MP 3A 3C propellers fitted to AIR TRACTOR AT 502A aircraft Model HC B5MP 3C propellers fitted to AIR TRACTOR AT 503 and 602 aircraft Model HC B5MA 3D T propellers fitted to AIR TRACTOR AT 802 aircraft Issued 28 November 2013 Page 31 of 35 CAA of NZ Hartzell Series Model HC B5MP 3F propellers fitted to AIR TRACTOR AT 802 aircraft Model HC B5MA 5A propellers fitted to ANTONOV AN 38 aircraft Model HC B3TN 5V propellers fitted to AYRES S 2R aircraft Model HC B4TN 5NL 5PL propellers fitted to AYRES S 2R 1340 G 5 6 10 RSS R1820 T 6 11 15 34 45 65 aircraft Model HC B5MP 3C propellers fitted to AYRES S 2R HG T65 aircraft Model HC B3TN 3AE propellers fitted to AYRES S 2R T aircraft Model HC B3TN 5K propellers fitted to BAE JETSTEAM 137 aircraft
55. r indicates the presence or absence of an additional letter s that varies the basic propeller model This AD still applies regardless of whether these letters are present or absent in the propeller model designation To prevent failure of the propeller hub which could result in blade separation and loss of aircraft control accomplish the following 1 Perform an eddy current inspection of the area around the lubrication holes of the hub blade sockets per the instructions in paragraphs 3 A through to 3 A 3 d of Hartzell Propeller Inc Alert Service Bulletin ASB No HC ASB 61 297 revision 1 If any cracks are found replace the propeller hub before further flight If no cracks are found mark the propeller per the instructions in paragraph 3 A 5 a of ASB No HC ASB 61 297 Replacing the non suffix S N propeller hub with a propeller hub identified by an A or a B suffix letter in the propeller hub S N is a terminating action to the requirements of this AD Replacement propeller hub P Ns can be found in paragraph 2 A of ASB No HC SB 61 297 2 Propeller hubs which have have been removed from an affected propeller with a non suffix S N or a E suffix in the S N shall not be fitted to any engine on any aircraft FAA AD 2008 13 28 refers 1 Within the next 50 hours TIS or by 31 July 2009 whichever occurs sooner unless previouly accomplished within the last 50 hours TIS and thereafter at intervals not to exceed 50 hours TIS
56. r occurs first since last inspection 3 Thereafter perform repetitive dye penetrant inspections of the blade internal bearing bore This repetitive blade internal bearing bore inspection is required at intervals not to exceed 60 months since last inspection D The initial inspection of the internal blade bearing bore required by paragraphs A 1 B 1 or C 1 of this AD need not be accomplished again if previously accomplished per page 4 of SB HC SB 61 217 Revision 1 E If not previously accomplished shot peen the propeller blade shank area during the initial inspection required by paragraphs A 1 B 1 or C 1 as applicable and perform the shot peening per SB HC SB 61 217 Revision 1 Re shot peening of the propeller blade shank area during the repetitive inspections required by paragraphs A 2 B 2 or C 2 as applicable is required only if the propeller blade shank area has been repaired or has excessive wear or damage per SB HC SB 61 217 Revision 1 Issued 28 November 2013 Page 17 of 35 CAA of NZ Compliance Effective Date DCA HARTZ 140 Applicability Requirement Note Compliance Effective Date Hartzell Series F Replacement of affected propellers or modification tio Hartzell model MV series propellers constitutes terminating action for the intitial and repetitive inspections specified in paragraphs A through E of this AD Hartzelll MV series propellers were certified as models HC 2 3 MV and
57. raft Model HC B3TF 7A propellers fitted to SIAI MARCHETTI AERMACCHI SM 1019 aircraft Model HC B3TF 7A propellers fitted to SIAI MARCHETTI VULCANAIR SF600 CANGURO aircraft Model HC B5MP 3 F propellers fitted to THRUSH AIRCRAFT S 2R T660 aircraft Model HC B3TN 5FL 5NL TWIN COMMANDER 690A 690B and 690C aircraft Model HC B3TF 7A propellers fitted to VALMET L 90TP aircraft Model HC B3TF 7A propellers fitted to VUCANAIR PARTENAVIA AP68TP 300 and 600 aircraft Affected propellers are known to be installed on but not limited to the above mentioned aircraft models This AD is also applicable to all other aircraft fitted with affected steel hub turbine propeller models with counterweight slug bolts P N B 3386 14H from LFC manufacturing lot 224 To prevent separation of a propeller blade counterweight slug which could result in injury and damage to the aircraft determine if propeller blade counterweight slug bolts P N B 3386 14H from LFC manufacturing lot 224 are fitted to the propeller If affected counterweight slug bolts are fitted to the propeller replace the bolts with serviceable bolts before further flight For the purpose of this AD a serviceable counterweight slug bolt is a P N B 3386 14H bolt from a LFC manufacturing lot other than lot 224 Accomplish the identification removal and replacement requirements in this AD per paragraphs 3 A 1 through to 3 A 4 b 5 in Hartzell Propeller Inc ASB No HC ASB 61 313 revision 2 da
58. ropeller Governors Hartzell Series HC B5MP5 EZ J pp HC B5MA 3 HBO Ia PERE EP PRICE IP RP EE Replacement March Sept Sept Sept E Fe by end 2000 2000 2001 2002 Hub Model Number S N Series HC B5MP 3 T HC B3TN 3 5707 Se 6742 rn 7864 a 8987 7 o 10409 11832 HE o ee a e e e HC B3MN5 Fz Hesna k gt pp fe PP HC B3TN 2 AG 239244 245 295 296 351 AA ES AE EA F R AA E A IES Y PEE E A VTA ES HO B4MP 4 Papes beer AAA A A gl HC B5MP 5 EZ Ja 194 _ M gt ee 178 O HC B5MA 3 29 52 53 78 79 1018 SA E A HC B5MN 3 HC B5MP 3 613 720 721 826 827 894 895 961 962 1002 1003 2030 HC B5MP 3 lene feer ot de T T O Replacement Sept March Sept Sept i due by end 2003 2004 2004 2005 a PPP e O te Number S N Series Hen B3TN 3 BU 11833 13488 15142 16300 17458 18309 eem a AE AE E E Ea PE NE NE EE EP EP Tras Je 7 Ea NN aaa E E A E A A eee HC B4TN 5 cD lA Hi i HC B4TN 3 EAT T e T e T HC B4MN 5 FLOP o T PP HC Bamp 3 FW pp T HC B4MP 4 FU ooo o T T e e FEE EGGE e NES e e HC B5MP 5 EZ PG HC B5MA 3 HB PP HC B5MN 3 ES TT HC B5MP 3 Ev pp pp HC B5MP 3 FTP E Effective Date 25 October 1996 Issued 28 November 2013 Page 15 of 35 CAA of NZ Propellers amp Propeller Governors Hartzell Series DCA HARTZ 139A Blades Rework and Inspection Applicability Requirement Model HC 2 3
59. rtains to the subject of this AD FAA AD 2003 03 20 refers 1 By 2000 hours TTIS 2 From 30 October 2008 3 From 30 October 2008 DCA HARTZ 141 27 February 2003 DCA HARTZ 141A 30 October 2008 Two Bladed Aluminium Hubs Replacement Model HC 2Y propellers with propeller hub P N D 6522 1 D 6522 2 D 6529 1 and D 6559 3 and the S N listed in the following table Table 1 Propeller S N Hub S N Hub P N AU11115B A61365B D 6522 1 AU11116B A61366B D 6522 1 AU11117B A61367B D 6522 1 AU11119B A61369B D 6522 1 AU11125B A61375B D 6522 1 AU11131B A61381B D 6522 1 AU11134B A61384B D 6522 1 AU11135B A61385B D 6522 1 AY515B A61397B D 6522 2 AY516B A61398B D 6522 2 CH36140B A61409B D 6529 1 CH36141B A61410B D 6529 1 CH36151B A61420B D 6529 1 CH36152B A61421B D 6529 1 Issued 28 November 2013 Page 19 of 35 CAA of NZ Requirement 1 CH36153B A61422B CH36157B A61427B EU376B A61443B CH36172B A61547B CH36159B A61553B CH36160B A61554B CH36162B A61556B CH36163B A61557B CH36165B A61560B CH36188B A61563B CH36193B A61568B CH36194B A61569B CH36195B A61570B CH36196B A61571B CH36178B A61573B CH36179B A61574B CH36181B A61576B CH36182B A61577B CH36183B A61578B CH36198B A61583B CH36199B A61584B CH36200B A61585B CH36201B A61586B CH36202B A61587B CH36203B A61588B CH36204B A61589B CH36205B A61590B CH36209B A61594B Propeller S N Hub S N CH36211B A61596B CH36212B A61597B CH36213B A61598B CH36215B A61601B CH36216B
60. s P N B 3339 that are not from LFC Manufacturing Lot No 12 or Lot No 56 or other equivalent manufacturer approved bolts per the instructions in paragraph 3 C of ASB HC ASB 61 279 Accomlishment of requirement 2 is a terminating action to the requirements of this AD FAA AD 2005 14 12 refers 1 Within 50 hours TIS or by 29 September 2006 whichever occurs first and thereafter torque check of all eight mounting flange bolts at intervals not to exceed 100 hour TIS 2 By 29 September 2006 29 September 2005 Goodrich FASTprop De icers Inspection and Replacement Goodrich De icing and Specialty Systems FASTprop propeller de icers P Ns P4E1188 series P4E1601 series P4E2200 series P4E2271 10 P4E2575 7 P4E2575 10 P4E2598 10 P5855BSW P6199SW P6592SW P6662SW and P6975 11 These propeller de icers are installed on but not limited to the aircraft listed in table 1 of FAA AD 2005 18 20 To prevent propeller de icers from detaching from the propeller blade resulting in damage to the aircraft and possible injury to passengers and crewmembers accomplish the following 1 Inspect propeller de icers per the accomplishment instructions in paragraphs 2 A 3 through to 5 of Goodrich De icing and Specialty Systems Alert Service Bulletin ASB No 30 60 00 1 Repair or replace as required before further flight 2 Inspect propeller de icers per the Pre flight Walkaround Visual Check in paragraph 2 A 2 of ASB No 3
61. ted 27 March 2009 FAA AD 2009 10 14 refers Within the next 50 hours TIS unless previously accomplished 25 June 2009 Propellers Hubs Inspection and Replacement Model HC 2Y K R series propellers fitted with propeller hubs without a S N suffix and those propeller hubs with an E S N suffix that are fitted to Lycoming O IO LO LIO TO LTO AIO AEIO and TIO 360 engine series This AD supersedes DCA HARTZ 153 to expand the propeller and engine applicability The parentheses in the propeller model number indicates the presence or absence of an additional letter s which varies the basic propeller model designation This AD still applies regardless of whether these letters are present or absent in the propeller model designation To prevent failure of the propeller hub which could result in blade separation and loss of aircraft control accomplish the following Perform an eddy current inspection ECI of the front cylinder half of the propeller hub for cracks per the instructions in paragraphs 3 A through to 3 A 4 g of Hartzell Propeller Inc SB No HC SB 61 269 revision 3 dated 17 September 2007 If any cracks are found replace the propeller hub before further flight If no cracks are found mark the propeller to indicate initial AD compliance per the instructions in paragraph 3 A 6 a of SB No HC SB 61 269 Do not repetitively mark the propeller once it is initially marked per the requirements of
62. ted blades Install blades incorporating strengthened pitch change knob identified with letter F per Hartzell SB 101 By 1200 hours TIS Blades with 1000 hours or more TIS within next 200 hours TIS 18 September 1974 Blades Inspection and Shot Peening Models HC 92WK and HC 92ZK series propellers which may be installed on but not limited to Beech 95 series Cessna 172 175 Mooney M20A Piper PA 23 PA 24 PA 25 and Lake LA 4 To prevent propeller blade separation accomplish the following 1 Inspect blade clamp screw per Procedure No 1 of Hartzell SB 202 If any clamp screws are found loose or broken remove propeller and send to a repair organisation for disassembly and inspection per Procedure No 2 of SB 202 If cracks are found during a dye penetrant inspection of the blade shank replace with a serviceable blade that has been compressively rolled in the blade shank 2 Send to a repair organisation for disassembly and inspection per Procedure No 2 of SB 202 If cracks are found during a dye penetrant inspection of the blade shank replace with a serviceable blade that has been compressively rolled in the blade shank FAA AD 95 11 08 refers 1 Within next 25 hours TIS 2 At 300 hours TIS since last dye penetrant inspection or compliance with DCA HARTZ 168 or within next 25 hours TIS whichever is the later Thereafter at intervals not to exceed 500 hours TIS DCA HARTZ 126 18 September 1974 DCA HARTZ 126
63. this AD Issued 28 November 2013 Page 33 of 35 CAA of NZ Note 3 Note 4 Note 5 Note 6 Note 7 Compliance Effective Date Hartzell Series Hartzell Propeller SB No HC SB 61 269 revision 4 dated 13 November 2009 is approved as an alternate method of compliance with DCA HARTZ 159 Any propeller hub P N D 6522 1 retired from service by AD DCA HARTZ 142 FAA AD 2003 01 03 refers must not be returned to service with the accomplishment of this AD This AD is not applicable to model HC 2Y K R series propellers fitted to aerobatic aircraft including certificated aerobatic aircraft military trainers or any aircraft routinely exposed to aerobatics agricultural aircraft Piper PA 32 series aircraft fitted with Lycoming 540 series reciprocating engines rated at 300 hp or higher and Britten Norman BN 2 series aircraft fitted with Lycoming 540 series reciprocating engines AD DCA HARTZ 134F FAA AD 2001 23 08 refers is applicable to these aircraft and addresses the same unsafe condition The repetitive inspections required by this AD can be terminated if the propeller hub without a S N suffix is replaced with a propeller hub identified with an A or B S N suffix Do not install a suffix A propeller hub that was previously installed on an aircraft affected by the original issue or later revision of Hartzell Propeller Inc SB No HC SB 61 227 Replacement propeller hub P N can be found in the material informatio
64. tion of the blade an optical comparator inspection of the blade retention area a visual and magnetic particle inspection of the blade clamp and a dye penetrant inspection of the blade internal bearing bore The initial inspection is required within the following i 1 000 hours TSN for propellers with less than 800 hours TSN provided that the initial inspections are performed within 60 months TSN or within next 24 months whichever calendar time occurs later or ii 200 hours TIS for propellers with 800 or more hours TSN or unknown TSN provided that the initial inspections are performed within the next 24 months 2 Thereafter perform repetitive fluorescent dye penetrant and eddy current inspection of the blade an optical comparator inspection of the blade retention area and a visual and magnetic particle inspection of the blade clamp The repetitive inspection is required at intervals not to exceed 500 hours TIS or 60 months whichever occurs first since last inspection 3 Thereafter perform repetitive dye penetrant inspections of the blade internal bearing bore This repetitive blade internal bearing bore inspection is required at intervals not to exceed 60 months since last inspection C For hub models HC A3VF 7 perform initial and repetitive inspections and if necessary replace with serviceable parts per SB HC SB 61 217 Revision 1 as follows 1 Initially perform a fluorescent dye penetrant and eddy current inspection

Hartzell Series - Civil Aviation Authority of New Zealand

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