Piper PA-34 Series - Civil Aviation Authority of New Zealand
Contents
1. Requirement Compliance Effective Date Model PA 34 200 S N 34 7250001 through 34 7450220 and PA 34 200T S N 34 7570001 through 34 8170065 Inspect and torque bolts replace parts or modify as necessary per Piper SB 699 Within the next 50 hours TIS 10 July 1981 DCA PA34 16 Cancelled DCA PA34 37 refers Effective Date 29 October 2009 DCA PA34 17 Exhaust System Heat Exchanger Inspection Applicability Requirement Compliance Effective Date Model PA 34 200 S N 34 7350342 through 34 7450220 Also 34 7250001 through 34 7350342 with kit 760 764V installed per Piper SL 673 To preclude possible engine power loss or stoppage inspect per Piper SB 762 FAA AD 83 14 05 refers At 1000 hours TTIS or within next 50 hours TIS whichever is the later and thereafter at intervals not exceeding 100 hours TIS 19 August 1983 DCA PA34 18D Cancelled DCA PA34 33 refers Effective Date 29 October 2009 DCA PA34 19 Cancelled DCA PA34 38 refers Effective Date 29 October 2009 Issued 28 February 2013 Page 6 of 18 CAA of NZ Aeroplanes Piper PA 34 Series Seneca I Il II IV and V DCA PA34 20 Rudder Torque Tube Assembly Inspection and Modification Applicability Requirement Compliance Effective Date Model PA 34 200 S N 34 7250001 through 34 7450220 PA 34 200T S N 34 7570001 through 34 8170092 PA 34 220T S N 34 8133001 through 34 8533012 Inspect and modify rudder torque tub2. 2 that meets the following conditions Issued 28 February 2013 Page 10 of 18 CAA of NZ Aeroplanes Compliance Effective Date Piper PA 34 Series Seneca I Il III IV and V e Was manufactured anytime from January 1997 through September 1998 and e Is identified with a 1 4 inch high white ink stamp FACET 638873 and may include FAA PMA Note Piper SB 1022 and Purolator SB 090298 01 provide information relating to this AD including procedures on how to identify the affected air filters FAA AD 99 05 09 refers Within next 25 hours TIS 25 March 1999 DCA PA34 29 Cancelled Superseded by DCA PA34 32 Effective Date 23 February 2006 DCA PA34 30_ Vertical Fin Inspection Applicability Requirement Compliance Effective Date DCA PA34 31 Applicability Requirement Compliance Effective Date Model PA 34 200 S N 34 7250001 through 34 7450220 PA 34 200T S N 34 7570001 through 34 8170092 PA 34 220T S N 34 8133001 through 3447029 and 3449001 through 3449284 This AD is not applicable to aircraft fitted with New Piper Kit 767 369 To maintain structural integrity of the vertical fin accomplish the following Inspect vertical fin rivets and perform the gap measurement per Piper SB 1130 If the gap measurement is larger than 0 032 inches or if there are loosened shanked and or failed rivets found during the inspection incorporate New Piper Kit 767 369 before further flight Wi
3. 664 Within the next 100 hours TIS 1 July 1974 Engine Nacelles Fuel Line Chafing Modification S N 34 7250001 through 34 7450209 Piper SB 429 FAA AD 74 17 08 refers Within the next 50 hours TIS 16 October 1974 Forward Baggage Door Inspection and Modification Model PA 34 200 Part and II of SB 447 S N 34 7250001 through 34 7450220 Part Il of SB 447 S N 34 7250001 through 34 7350265 Piper SB 447 1 Part I within the next 10 hours TIS 2 Parts Il and III within the next 50 hours TIS 17 April 1975 DCA PA34 8A Quick Disconnect Seat Retention Mechanism Inspection Applicability Requirement Compliance Effective Date All model PA 34 fitted with removable passenger seats having quick disconnect floor fittings Piper SL 763 FAA AD 75 24 02 refers Within the next 100 hours TIS and thereafter annually 17 December 1975 Note AD Supplement DCA PA34 8 is hereby cancelled and the placard which it required may be removed when seat retention has been checked as satisfactory per SL 763 Issued 28 February 2013 Page 4 of 18 CAA of NZ Aeroplanes Piper PA 34 Series Seneca I Il III IV and V DCA PA34 9 Usable Fuel Quantity Placard Applicability Model PA 34 200 S N 34 7250001 through 34 7450220 Requirement Document Piper SB 438 FAA AD 75 20 03 refers Compliance Within the next 50 hours TIS Effective Date 30 September 1975 DCA PA34 10 Engine Controls Inspection Applicability Model PA
4. 7250001 through to 34 7450220 Model PA34 200T aircraft S N 34 7570001 through to 34 8170092 Model PA34 220T aircraft S N 34 8133001 through to 34 8233088 not fitted with trunnion housing assemblies Piper P N 39486 802 left and P N 39486 803 right with embossed forging number 67924 2 This AD revised to remove the 50 hour repetitive inspection for requirement 1 of this AD for MLG trunions with more than 2000 hours TTIS There is no change to the AD requirement No action required if already in compliance with DCA PA34 33 This AD supersedes both DCA PA34 18D and DCA PA34 23A with the issue of Piper SB No 787C and the issue of FAA Special Airworthiness Information Bulletin SAIB No CE 04 89 dated 17 September 2004 This AD is not applicable to trunnions embossed with forging number 02599 02 The CAA endorses FAA SAIB No CE 04 89 which alerts operators to the requirements of Piper SB No 787C and the possibilty of cracks developing in trunnions with more than 2000 hours TTIS Issued 28 February 2013 Page 12 of 18 CAA of NZ Aeroplanes Requirement Note 3 Note 4 Compliance Effective Date Piper PA 34 Series Seneca I Il III IV and V To prevent collapse of the main landing gear due to possible cracked trunnions accomplish the following 1 Inspect the MLG trunnions for cracks using dye penetrant per the instructions in Piper SB No 787C Blend out any grinding marks in the web area as shown in Piper SB No
5. 787C using aluminum oxide paper 300 grit or finer or an equivalent material before further flight Alodine and repaint the areas where grinding marks are blended out Replace cracked MLG trunnions with applicable parts of improved design P N 67926 30 67926 31 67926 32 67926 33 39486 14 39486 15 or later manufacturer approved parts in accordance with the applicable maintenance manual 2 Replace both MLG trunnions with applicable parts of improved design P N 67926 30 67926 31 67926 32 67926 33 39486 14 39486 15 or later manufacturer approved parts in accordance with the applicable maintenance manual Replacing both the left and right MLG trunnion with applicable parts of improved design P N 67926 30 67926 31 67926 32 67926 33 39486 14 39486 15 or later manufacturer approved parts is a terminating action to the repetitive inspection requirements of this AD Accomplish the requirements of this AD per the instructions in Piper SB No 787C dated 7 November 2000 FAA AD 94 13 11 refers 1 At 500 hours TTIS on affected MLG trunnions or within the next 100 hours TIS whichever is the later and thereafter at intervals not to exceed 100 hours TIS until 2000 hours TTIS and accomplishment of requirement 2 of this AD For the initial inspection if the hours TTIS on the MLG trunnions cannot be determined the aircraft hours TTIS may be used 2 At 2000 hours TTIS on affected MLG trunnions or within the next 100 hours TIS whic
6. 95643 06 95643 07 95643 08 or 95643 09 as applicable No repetitive inspections will be required by this AD for when this bracket assembly is installed on both the LH and RH sides or Ream the existing two piece bushings P N 67026 6 to an inside diameter of 624 inch to 625 inch chamfer the head side of the bushing to accommodate the radius in the shank of the main gear sidebrace stud and install the 5 8 inch stud P N 78717 02 No repetitive inspections will be required by this AD when this action is accomplished on both the LH and RH bracket assemblies If the bushings cannot be reamed while installed in the bracket i e the bushings are loose then install a main gear sidebrace bracket assembly P N 95643 06 95643 07 95643 08 or 95643 09 as applicable The repetitive inspections mandated by this AD may be terminated at any time when one of the following is accomplished 1 Install a main gear sidebrace bracket assembly P N 95643 06 95643 07 P N 95643 08 or 95643 09 as applicable which contains the 5 8 inch diameter main gear sidebrace stud P N 78717 02 and the one piece bushing P N 67026 12 or 2 Ream the existing two piece bushings P N 67026 6 to an inside diameter of 624 inch to 625 inch chamfer the head side of the bushing to accommodate the radius in the shank of the main gear sidebrace stud and install the 5 8 inch stud P N 78717 02 If the bushings cannot be reamed while installed in the bracket i e the bushings are l
7. CAA of NZ Aeroplanes DCA PA34 1 Applicability Requirement Compliance Effective Date DCA PA34 2 Applicability Requirement Compliance Effective Date DCA PA34 3 Applicability Requirement Compliance Effective Date Piper PA 34 Series Seneca I Il III IV and V Aft Wing Assembly Inspection All PA 34 200 aircraft Inspection may be cancelled when aft wing modification kit Piper P N 760 696V has been installed and the inspection and reservicing of the main landing gear has been accomplished in accordance with Piper Service Bulletin 406 1 Visually inspect both left and right wing lower surface skins for wrinkling immediately outboard of the wheel well openings Note The Maintenance Release may be endorsed authorising the pilot to carry out the inspection referred to in 1 above provided he has been suitably instructed by an appropriately licensed LAME 2 If wrinkles are present visually check the wing ribs located at the outer end of the wheel wells wing station 69 24 for cracks and wrinkles in the web These cracks or wrinkles emanate from the forward lower corner where the rib attaches to the main spar and may propogate towards the aft upper corner of the web 3 If wrinkles are present and aft wing modification kit Piper P N 760 696V has not been installed check the area where the main landing gear aft trunnion fitting attaches to the aft false spar for cracks 4 If cracks or wrinkl
8. Piper Kit Number 760 722V per Piper SB No 374 dated 16 February 1973 before further flight Reassemble the induction air boxes and install and rig in accordance with the PA 34 service manual FAA AD 1972 17 01 refers Compliance Within the next 100 hours TIS unless previously accomplished and thereafter at intervals not to exceed 100 hours TIS Effective Date 29 October 2009 Issued 28 February 2013 Page 15 of 18 CAA of NZ Aeroplanes Piper PA 34 Series Seneca I Il III IV and V DCA PA34 37 Engine Hose Assemblies Inspection and Renewal Applicability Note Requirement Compliance Effective Date Model PA 34 200 aircraft all S N fitted with STC SA2937WE This AD supersedes DCA PA34 16 to correct the STC number in the applicability To prevent failure of the engine air fuel and or oil hoses which could result in fire accomplish the following Inspect the engine fuel air and oil hose assemblies listed in Rajay SL No 28 dated 3 August 1981 and determine the general condition and age of the hose assemblies based upon the metal plate attached to the hose If the hose assembly is five years old or older replace with an equivalent serviceable part before further flight If the hose assembly does not have a metal tag and the age cannot be determined replace with an equivalent serviceable part before further flight Record hose ages in the aircraft engine log book and determine a hose replacement sched
9. heater fuel pump To prevent combustion heater fuel pump fuel leakage which could result in failure of the pump and fire or explosion inspect the aircraft heater fuel pump model 91E92 1 or model 91E93 1 for leakage per The New Piper Aircraft Inc Service Bulletin No 1127B dated 18 April 2005 and Kelly Aerospace Power Systems Service Information Letter Bulletin No A 110B dated 20 December 2004 If any leak is found inspect the pump sealing surface for abnormalities for example nicks gouges or warping Correct any abnormality per SB 1127B and SIL A 110B prior to further flight If any abnormality cannot be corrected replace the header fuel pump prior to further flight Before installing a model 91E92 1 or model 91E93 1 heater fuel pump visually inspect the pump and correcting any abnormalities per SB 1127B and SIL A 110B Inspections and corrections which have already been accomplished per SB 1127 dated 26 February 2003 and SIL A 110A dated 6 March 2003 are acceptable FAA AD 2005 15 10 refers Within the next 10 hours TIS unless already accomplished 23 February 2006 DCA PA34 33A MLG Trunnions Inspection and Replacement Applicability Note 1 Note 2 The following aircraft models and S N not fitted with MLG trunnions both left and right side P N 67926 30 67926 31 67926 32 67926 33 39486 14 or 39486 15 embossed with forging number 02599 02 as applicable Model PA34 200 aircraft S N 34
10. of this AD depicts the area where the sidebrace stud is to be inspected 2 95 20 07 Main Landing Gear Leg Actuator Main Landing Gear Sidebrace Stud Sidestay Assembly Support Bracket bolted to Forward Spar Sidestay Assembly Upper Link Downlock Switch hidden Sidestay Assembly Lower Link Fracture Crack Position Figure 1 Note This figure is provided to depict the area of the sidebrace stud to be inspected This is not intended to represent the configuration of all models affected For any main gear sidebrace stud not found cracked before to further flight reinstall the stud per the instructions in the Landing Gear section of the applicable MM and reinspect and replace as necessary per this AD Issued 28 February 2013 Page 8 of 18 CAA of NZ Aeroplanes Note 3 Compliance Effective Date Piper PA 34 Series Seneca I Il III IV and V For any main gear sidebrace stud found cracked before to further flight replace the cracked stud with a serviceable part per the instructions in the Landing Gear section of the applicable MM and accomplish one of the following as applicable Reinspect and replace as necessary per the repetitive requirements in this AD or For affected PA34 200 and PA34 200T aircraft the 9 16 inch main gear sidebrace studs P N 95299 00 95299 02 or 67543 as applicable are no longer manufactured Install a new main gear sidebrace stud bracket assembly P N
11. 1 DCA PA34 30 Vertical Fim INSPOCtlON sic iceccdsdicesteesseseazasacassaecepecscecczsaacadasachsapeassenadegdeeecpbasi aAA 11 DCA PA34 31 Control Wheel Attachment Inspection and Modification 0 0 ccceseeeeseeeeeeeeeeeeeneereaes 11 DCA PA34 32 Combustion Heater Fuel Pump Inspection 0 0 eeeeeeeeeeseeeeeeeeeneeeeeeeeeeeeeeeeeeeeeeeeeenes 12 DCA PA34 33A MLG Trunnions Inspection and Replacement ceeccceeseeeeeeteeeeeeneeteeeeetereaeeeeaeens 12 Issued 28 February 2013 Page 1 of 18 CAA of NZ DCA PA34 34 Nose Landing Gear Inspection and Maintenance ccccceeeceeeeeeeeeeeeeeeeeeeeeteeeeeneees 13 DCA PA34 35 Airworthiness Directive Compliance cccceeceeeceeeeeeeeeeeeeeeeeeeeeeseaeeeeeeeseaeeseeeestaeeeeeeenes 15 DCA PA34 36 Induction Air Box Valves Inspection and REWOKK ccescceeesseeeeeeeneeeeseneeeeteneeenenaees 15 DCA PA34 37 Engine Hose Assemblies Inspection and Renewal cscccssseeessseeesesseeeeeeneeereeaes 16 DCA PA34 38 Forward Baggage Compartment Door Inspection and Modification c0ccee 16 DCA PA34 39 Control Wheel Shafts Inspection and Rework esceeeseeceeeeseneeeeeeteaeeteaeeteeeeeaeernes 17 http www caa govt nz Airworthiness Directives states of design html 2013 02 13 Horizontal Stabilator Control System INSPeCtION eee eeceeeeeeeeeeeeeeeeeeeeeeeeeeeteeeeneees 18 Issued 28 February 2013 Page 2 of 18
12. 34 200 S N 34 7250001 through 34 7450220 Requirement Piper SB 548 FAA AD 77 23 03 refers Compliance Within the next 50 hours TIS Effective Date 31 March 1978 DCA PA34 11C Cancelled DCA PA34 38 refers Effective Date 29 October 2009 DCA PA34 12 Avionics Master Relay Wiring Inspection Applicability Model PA 34 200T S N 34 7670001 through 34 8070001 Requirement Inspect per Piper SB 668 and secure wiring as necessary Compliance Within the next 50 hours TIS Effective Date 21 December 1979 DCA PA34 13_ Radio Installation Modification Applicability Model PA 34 200T S N 34 7870001 through 34 8070150 with Bendix King or Narco transmitters and factory installed control wheel push to talk switches Requirement Modify per Piper SB 681 Part II FAA AD 80 14 03 refers Compliance Within the next 100 hours TIS or by 31 October 1980 whichever is the sooner Effective Date 1 August 1980 Issued 28 February 2013 Page 5 of 18 CAA of NZ Aeroplanes Piper PA 34 Series Seneca I Il III IV and V DCA PA34 14B Ammeter Installation Modification Applicability Requirement Compliance Effective Date Model PA 34 200T S N 34 7570001 through 34 8170092 Modify per Piper SB 811A unless aircraft equipped with 90 ampere alternator FAA AD 86 17 01 refers By 28 February 1987 DCA PA34 14A 22 October 1982 DCA PA34 14B 14 November 1986 DCA PA34 15 Rudder Torque Tube Assembly Inspection Applicability
13. Airworthiness Directive Schedule Aeroplanes Piper PA 34 Series Seneca I Il Ill IV and V 28 February 2013 Notes 1 This AD schedule is applicable to Piper PA 34 200 Seneca I PA 34 200T Seneca Il PA 34 220T Seneca Ill IV and V aircraft manufactured under Federal Aviation Administration FAA Type Certificate No A7SO 2 The Federal Aviation Administration FAA is the National Airworthiness Authority NAA responsible for the issue of State of Design Airworthiness Directives ADs for Piper PA 34 series aircraft State of Design ADs applicable to these aircraft 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 New or amended ADs are shown with an asterisk Contents DCA PA34 1 Aft Wing Assembly Inspection eee eeeeeeeeneeeeeeneeeeeneeeeeenaeeeeeeaeeeeseaeeeeeenaeeeeeeaeeeenenneeees 3 DCA PA34 2 Rudder Servo Trim Tab Inspection ccceeceeceeeeeeeeeteeeeeeeeeeeeeeeeeeeseaeeeeeeeseaeeeeeeeseaeeteeeenea 3 DCA PA34 3 Exhaust System Inspectionistciecidn died dandieliiacivaiinai ibe eaiieienade 3 DCA PA34 4 Glove Compartment Modification eeceeeceeeeeeeneeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeseeeeeieeeeneees 4 DCA PA34 5 Wing Skin Rib Inspection and Modification cccceeeeeseeeeeeeeseeeeteeeseeeseeeseneeseeetenes 4
14. DCA PA34 33 refers Effective Date 29 October 2009 DCA PA34 24 Cancelled DCA PA34 34 refers Effective Date 29 October 2009 Issued 28 February 2013 Page 7 of 18 CAA of NZ Aeroplanes Piper PA 34 Series Seneca I Il III IV and V DCA PA34 25B Main Landing Gear Sidebrace Stud Inspection Applicability The following model and S N aircraft not fitted with a main landing gear side brace stud P N 78717 02 in both LH and RH main landing gear sidebrace bracket assemblies Model PA 34 200 aircraft all S N Model PA 34 200T aircraft S N 34 7570001 through to 34 7770372 Note 1 There is no change to the AD requirement This AD revised to clarify and align the AD requirement with FAA AD 97 01 01R1 Note 2 The Appendix included in FAA AD 97 01 01R1 contains information to determine the P N of the main gear sidebrace stud assembly which contains the main gear side brace stud on affected PA34 200 and PA34 200T aircraft Requirement To prevent main landing gear MLG collapse due to possible main gear sidebrace stud cracks which if not detected and corrected could result in loss of aircraft control during landing accomplish the following Remove both the left and right main gear sidebrace studs from the aircraft per the instructions in the landing gear section of the aircraft MM Inspect both the main gear sidebrace stud for cracks using Type fluorescent liquid penetrant or magnetic particle inspection methods Figure 1
15. DCA PA34 6 Engine Nacelles Fuel Line Chafing Modification c cecceeeseesseeeeeeeeseeeeeeeeeteeeeeeeeeeee 4 DCA PA34 7 Forward Baggage Door Inspection and Modification cccecceeeeeeeeeeeteeeeeeeeeeeeeee 4 DCA PA34 8A Quick Disconnect Seat Retention Mechanism Inspection csceeeeeeeeeeeeeeeeteneeeeneerenes 4 DCA PA34 9 Usable Fuel Quantity Placard eeeececeeeeeeeeneeeeneeeeneeseaeeteaeeeeaeeseaeeeeaeeseaeeseaeeteeeseaeetias 5 DCA PA34 10 Engine Controls INSD CtiON ccceeeceeeseeeeeeeeeneeeeeeeeeaeeeeaneseaeeeeaeeseaeeseaeeeeeeseeeeseneeeeeeetens 5 DCA PA34 11C Cancelled DCA PA34 38 refers cecceecceeseeeeeeeeeeeeeteeeeeseeeseaeeesaeessaeeesaeesaeeeeeeseaeeeatens 5 DCA PA34 12 Avionics Master Relay Wiring Inspection eee eeeeeeeeenneeeeeeeeeeteneeeeeenneeeseeneeeneneeeees 5 DCA PA34 13 Radio Installation Modification 0 0 ee eeeeeeeeeeeeeeeneeeeeeeeeeseaeeeeesaeeeeesaeeeeseeeeeeenaeeesenaees 5 DCA PA34 14B Ammeter Installation Modification ce eeseeeeseeeeeeneeeeeneeeeeesaeeeeseaeeeeeenneeeeeeeeeeneeeeess 6 DCA PA34 15 Rudder Torque Tube Assembly Inspection eee eeeeeeseeeseneeeeeenaeeeeeeaeeeeteaeeeetenneeereaees 6 DCA PA34 16 Cancelled DCA PA34 37 refers cecccesceeeneteneeeeeeeceaeeseaeeseaeeseaeeseaeeseaeeseaeessaeeseeeseaeens 6 DCA PA34 17 Exhaust System Heat Exchanger INSP CtiON cecceeeceeseeeeeeeeeteeeeeeeeeteaeeteeeeseneee
16. III of Piper SB No 633B dated 3 October 1980 2 For model PA 34 200 aircraft S N 34 7250001 through to 34 7450220 and model PA 34 200T aircraft S N 34 7570001 through to 34 8070367 Modify the forward baggage door per the instructions in part IV of Piper SB No 633B dated 3 October 1980 Issued 28 February 2013 Page 16 of 18 CAA of NZ Aeroplanes Compliance Effective Date Piper PA 34 Series Seneca I Il III IV and V 3 For all affected aircraft visually inspect repair as required and modify the forward baggage compartment door and latching mechanism per the instructions in Piper SB No 872 dated 9 November 1987 FAA AD 1988 04 05 refers 1 Within the next 50 hours TIS unless previously accomplished 2 Within the next 50 hours TIS unless previously accomplished 3 Within the next 50 hours TIS unless previously accomplished 29 October 2009 DCA PA34 39 Control Wheel Shafts Inspection and Rework Applicability Requirement Note Compliance Effective Date Model PA 34 200 aircraft S N 34 E4 and 34 7250001 through to 34 7450220 Model PA 34 200T aircraft S N 34 7570001 through to 34 8170092 Model PA 34 220T aircraft S N 34 8133001 through to 34 8633031 3433001 through to 3433172 3448001 through to 3448037 3448038 through to 3448079 3447001 through to 3447029 and 3449001 through to 3449377 To prevent failure of the control wheel shafts due to possible incorrect assembly which can resu
17. SB No 367 refers 80 09 04 Vertical Fin and Stabiliser SB No 579 refers 82 04 08 Landing Gear Retraction SB No 732 refers 99 14 01 Severe Icing Conditions AFM amendment Note Each part of this AD each individual FAA AD shall be certified in the aircraft log book separately Compliance Before issue of a New Zealand Certificate of Airworthiness or at the next ARA inspection after the effective date of this AD whichever is the sooner unless previously accomplished Effective Date 29 October 2009 DCA PA34 36_ Induction Air Box Valves Inspection and Rework Applicability Model PA 34 200 aircraft S N 34 E4 and 34 7250001 through to 34 7350074 Note The requirements of this AD do not apply to those aircraft embodied with Piper Kit Number 760 722V in accordance with Piper SB No 374 dated 16 February 1973 Requirement To prevent failure of the induction air box valve which could result loss of engine power accomplish the following Remove the induction air box assembly from both engines and remove the valve assembly from the box assembly to permit a thorough visual inspection of the valve assembly Inspect the valve assembly for any evidence of excessive wear or cracks in the areas where the shaft mates to the valve assembly per Piper SB No 358 If the valve assemblies are found worn loose or cracked replace all affected parts with serviceable parts of the same P N per Piper SB No 358 before further flight or embody
18. ce washer Piper P N 407 564 or standard P N AN960 10 nut Piper P N 404 392 or standard P N AN320 3 and cotter pin Piper P N 424 051 or standard P N MS24665 132 as applicable per SB 965 FAA AD 96 10 03 refers Note The requirement of this airworthiness directive takes precedence over SB 965 instructions and requires installing the clevis bolt regardless of the condition of the current part At 2000 hours TTIS or within next 100 hours TIS whichever is the later 5 July 1996 DCA PA34 27 Cancelled DCA PA34 35 refers Note Effective Date DCA PA34 28 Applicability Requirement FAA AD 99 14 01 listed in DCA PA34 35 supersedes DCA PA34 27 29 October 2009 Induction Air Filters Removal from Service The following models and S Ns that are equipped with Purolator air filter P N 638873 Model CA161PL or Piper P N 460 632 PS60007 2 PA 34 200T S N 34 7570001 through 34 8170092 PA 34 220T S N 34 8133001 through 34 8633031 and 3433001 through 3433225 PA 34 220T S N 3448001 through 3448035 PA 34 220T S N 3448038 through 3448079 and 3447001 through 3447029 PA 34 220T S N 3449002 through 3449078 To prevent pieces of a damaged induction air filter from being ingested into the engine which could result in reduced or loss of engine power accomplish the following Replace per the maintenance manual any Purolator Facet induction air filter Purolator P N 638873 Model No CA161PL Piper P N 460 632 PS60007
19. dified parts that may be fitted to improve service life Note 3 The requirements in this AD may include one or a combination of the following actions replacement repair adjustment alignment cleaning lubricating or other action FWD UPPER DRAG LINK ASSY PART NUMBER 95728 00 LOWER DRAG LINK ASSY PART NUMBER 95729 00 BULKHEAD J BOLT NAS464 P620 WASHER AN960 616 NUT AN320 6 COTTER PIN MS244665 283 AN7 35 AN960 716 OR AN960 716L AN320 7 i MS24665 FWD TRUNNION RING BLOCK UPPER DRAG LINK ASSY SECTION B B UPPER DRAG LINK TO GEAR CONNECTION FAA AD 2005 13 16 refers Compliance 1 Within the next 100 hours TIS unless previously accomplished 2 Within the next 100 hours TIS unless previously accomplished and thereafter at the intervals specified in Piper SB No 1123B Effective Date 29 October 2009 Issued 28 February 2013 Page 14 of 18 CAA of NZ Aeroplanes Piper PA 34 Series Seneca I Il III IV and V DCA PA34 35_ Airworthiness Directive Compliance Applicability Model PA 34 200 PA 34 200T and PA 34 220T aircraft all S N Requirement Compliance with the following FAA Airworthiness Directives as applicable is required 72 14 07 Stabilator Hinge Fittings 72 18 06 Stabilator Tip Balance Weights 74 19 01 Outer Wing Spars No reference service info 75 25 03 Engine Oil SB No 483 refers SL No 614 refers 78 21 03 Fuel Lines SB No 596A refers
20. e assembly per Piper SB 899 FAA AD 92 08 04 refers Within the next 50 hours TIS 12 May 1989 DCA PA34 21A MLG Trunnion Attach Fittings Inspection Applicability Requirement Compliance Effective Date Model PA 34 200 S N 34 7250001 through 34 7450220 PA 34 200T S N 34 7570001 through 34 8170092 PA 34 220T S N 34 8133001 through 34 8633031 3433001 through 3433198 and 3448001 through 3448018 To preclude failure of the MLG attachment inspect per Part of Piper SB 956 and rectify if necessary per Part Il of the SB Within the next 100 hours TIS and thereafter at intervals not exceeding 100 hours TIS until modified per Part II of the SB DCA PA34 21 14 December 1989 DCA PA34 21A 30 April 1992 DCA PA34 22A NLG Centring Attachment Bolt Replacement Applicability Requirement Compliance Effective Date PA 34 200 S N 34 7250001 through 34 7450220 PA 34 200T S N 34 7570001 through 34 81 70092 To prevent a failure of the NLG to extend due to contact between the hex head bolt attaching the NLG centring spring rod end and the door actuation aft tube assembly accomplish the following 1 Replace the hex head bolt with clevis head bolt per Piper SB 893 unless already accomplished 2 Ensure that the placard required by part 6 of the SB is securely affixed FAA AD 92 13 05 refers Within next 100 hours TIS and whenever the NLG is replaced or refitted 25 August 2005 DCA PA34 23A Cancelled
21. eeeeeea 6 DCA PA34 18D Cancelled DCA PA34 33 refers eccceeceeeseeceneeeeeeeteaeeeeaeeseaeeseaeeseaeeeeaeeseaeeeeaeeteeeeeaters 6 DCA PA34 19 Cancelled DCA PA34 38 refers cccceecceesseceeeeseeeeeeeeeneeeseaeeesaeeseaeeesaeesaeeeeeeneaeeeaten 6 DCA PA34 20 Rudder Torque Tube Assembly Inspection and Modification eeeceseeeeeeeeeeeenees 7 DCA PA34 21A MLG Trunnion Attach Fittings INSD CtION c eecceeeeeeeeeeeeeeeeeeeeteeeeteeeeteaeeeeeeeteaeeeeeeenea 7 DCA PA34 22A NLG Centring Attachment Bolt Replacement ccceeeceeeceeeeeeeeneeeeeeeseneeeeeeeeeneeeeeeeeeas 7 DCA PA34 23A Cancelled DCA PA34 33 refers ceccesceeseeeseneeeseeeseeeeeseeeseaeeesaeesaeeesaeeseaeeeaeessaeeeaten 7 DCA PA34 24 Cancelled DCA PA34 34 refers eeccecesceeeeeeteneeceeeceaeeeeaeeteaeeseaeeseaeeenaeeseaeeseaeeseeeeeatens 7 DCA PA34 25B Main Landing Gear Sidebrace Stud Inspection eeeeeeeeeeeeeeeeeeeeeeeteneeteeeteeeeeaeetens 8 DCA PA34 26 Flap Lever and Bolt Inspection and Replacement escceesesceeeeeneeesenneeeeeeneeeteeaes 10 DCA PA34 27 Cancelled DCA PA34 35 refers cecceeceeseeeeeeeeeseeeeeeeeeseeeeeneeeseeesaeeseaeeseaeeseseeseeeeteaeee 10 DCA PA34 28 Induction Air Filters Removal from Service eccceesceeseeeeeeeeeeeeeeneeeeeeseeeseeeeseeeneaeene 10 DCA PA34 29 Cancelled Superseded by DCA PA34 32 ceccceesceeeeeeeneeteneereaeeteaeeteneeseaeeteneeeeeetenes 1
22. es are present in the areas described in 2 or 3 above replace affected parts with serviceable parts of the same P N or make an approved repair before further flight FAA AD 73 11 02 refers Within the next 10 hours TIS and thereafter at intervals not exceeding 10 hours TIS 31 July 1973 Rudder Servo Trim Tab Inspection S N 34 7250001 through 34 7450084 not incorporating Piper SL 714 Piper SB 390A FAA AD 73 13 01 refers Within the next 10 hours TIS and thereafter at intervals not exceeding 100 hours TIS 31 July 1973 Exhaust System Inspection S N 34 7250001 and up Piper SB 373A FAA AD 73 14 02 refers Within the next 10 hours TIS or before the accumulation of 60 hours TIS whichever occurs later and thereafter at intervals not exceeding 25 hours TIS 31 August 1973 Issued 28 February 2013 Page 3 of 18 CAA of NZ Aeroplanes DCA PA34 4 Applicability Requirement Compliance Effective Date DCA PA34 5 Applicability Requirement Compliance Effective Date DCA PA34 6 Applicability Requirement Compliance Effective Date DCA PA34 7 Applicability Requirement Compliance Effective Date Piper PA 34 Series Seneca I Il III IV and V Glove Compartment Modification S N 34 7250001 through 34 7450084 Piper SB 412 Within the next 100 hours TIS 31 May 1974 Wing Skin Rib Inspection and Modification S N 34 7250001 through 7250360 and 34 7350001 through 34 7350234 Piper SL
23. hever occurs later unless previously accomplished If the hours TTIS on the MLG trunnions cannot be determined the aircraft hours TTIS may be used DCA PA34 33 29 October 2009 DCA PA34 33A 25 March 2010 DCA PA34 34 Nose Landing Gear Inspection and Maintenance Applicability Note 1 Requirement Model PA 34 200 PA 34 200T and PA 34 220T aircraft all S N This AD supersedes AD DCA PA34 24 and introduces new NLG inspection and rigging procedures Accomplish the requirements in this AD per Piper SB No 1123B because to SB No 1123A is no longer active To prevent prevent failure of components of the NLG which could result in the NLG collapsing accomplish the following 1 Replace the bolt and stack up that connects the upper drag link to the nose gear trunnion with new Piper parts or approved equivalent parts per the figure in this AD Piper bolt P N 400 274 AN7 35 Piper washer P N 407 591 AN960 716L as applicable Piper washer P N 407 568 AN960 716 Piper nut P N 404 396 AN320 7 Piper cotter pin P N 424 085 Issued 28 February 2013 Page 13 of 18 CAA of NZ Aeroplanes Piper PA 34 Series Seneca I Il III IV and V 2 Inspect the NLG installation per the instructions in table 1 of Piper SB No 1123B dated 20 April 2006 If any defects are found accomplish all the required corrective actions in table 1 of SB No 1123B before further flight Note 2 Paragraph 2 in SB No 1123B specifies mo
24. lt in loss of pitch and roll control accomplish the following Inspect the pilot and copilot control wheel columns for correct shaft installation per the instructions in Piper Aircraft Inc MSB No 1197A dated 1 September 2009 or Piper Aircraft Inc MSB No 1197B dated 3 May 2010 If the control wheel shaft is found incorrectly installed replace with a new shaft per the instructions in MSB No 1197A or MSB No 1197B before further flight Inspect the universal joint and all the other control wheel parts for any deterioration excess wear and damage If any defects are found replace affected parts per the instructions in MSB No 1197A or MSB No 1197B before further flight Accomplish the requirements of this AD per the instructions in Piper Aircraft Inc MSB No 1197A dated 1 September 2009 or Piper Aircraft Inc MSB No 1197B dated 3 May 2010 FAA AD 2010 15 10 refers Within the next 100 hours TIS or by 31 August 2011 whichever occurs sooner 31 August 2010 Issued 28 February 2013 Page 17 of 18 CAA of NZ Aeroplanes Piper PA 34 Series Seneca I Il III IV and V http www caa govt nz Airworthiness Directives states of design html 2013 02 13 Horizontal Stabilator Control System Inspection Effective Date 11 March 2013 Issued 28 February 2013 Page 18 of 18 CAA of NZ
25. oose then install a main gear sidebrace bracket assembly P N 95643 06 95643 07 95643 08 or 95643 09 as applicable FAA AD 97 01 01R1 refers Within the next 100 hours TIS unless previously accomplished and thereafter at intervals not to exceed 500 hours TIS DCA PA34 25 24 November 1995 DCA PA34 25A 14 March 1997 DCA PA34 25B 29 September 2011 Issued 28 February 2013 Page 9 of 18 CAA of NZ Aeroplanes Piper PA 34 Series Seneca l Il III IV and V DCA PA34 26_ Flap Lever and Bolt Inspection and Replacement Applicability Requirement Compliance Effective Date Model PA 34 200 S N 34 7250001 through 34 7450220 PA 34 200T S N 34 7570001 through 34 8170092 and PA 34 220T S N 34 8133001 through 34 8233088 To prevent failure of the flap handle attach bolt and sudden retraction of the flaps which could result in loss of control of the aircraft accomplish the following Measure the cable mounting attach hole diameter and enlarge the hole to 0 316 inch diameter If the diameter of the cable mount attach hole is larger than 0 316 inch prior to further flight replace the flap lever handle per Piper SB 965 Install a new bushing using Piper P N 63900 174 into the cable mounting attach hole per SB 965 Replace the flap lever handle attach bolt with a new clevis bolt Piper P N 400 673 or standard P N AN23 11 per SB 965 Inspect the washer nut and cotter pin and if damaged prior to further flight repla
26. thin next 100 hours TIS 29 July 2004 Control Wheel Attachment Inspection and Modification Group A PA 34 220T S N 3449042 through 3449292 Group B PA 34 220T S N 3449293 through 3449301 To detect and correct inadequate control wheel attachment design which could result in loss of control accomplish the following 1 For aircraft listed in Group A inspect the control wheel attachment screw and nut plate for proper thread engagement minimum one thread showing past the end of the nut plate and replace the screw and or nut plate if insufficient thread engagement is found Reassemble the control wheel onto the control wheel shaft and apply Loctite thread locking compound 2 For Group A and B aircraft install the retainer clip P N 104687 002 per Part II of New Piper Aircraft SB 1139A FAA AD 2004 14 12 refers 1 Inspect within 25 hours TIS 2 Install the retainer clip within 100 hours TIS 26 August 2004 Issued 28 February 2013 Page 11 of 18 CAA of NZ Aeroplanes Piper PA 34 Series Seneca I Il III IV and V DCA PA34 32 Combustion Heater Fuel Pump Inspection Applicability Requirement Note 1 Note 2 Compliance Effective Date Model PA 34 200T aircraft S Ns 34 7570002 through 34 81 70092 and Model PA 34 220T aircraft S Ns 34 8133002 through 3449278 and Model PA 34 220T aircraft S Ns 3449279 through 3449309 and fitted with either a model 91E92 1 or model 91E93 1 aircraft
27. ule to ensure the five year life limitation will not be exceeded If the hose assembly is deteriorated regardless of age replace with a serviceable part before further flight FAA AD 1981 19 04 refers Within the next 100 hour TIS or at the next annual inspection whichever occurs first unless previously accomplished and thereafter at intervals not to exceed 60 months 29 October 2009 DCA PA34 38 Forward Baggage Compartment Door Inspection and Modification Applicability Note Requirement Model PA 34 200 aircraft S N 34 7250001 through to 34 7450220 Model PA 34 200T aircraft S N 34 7570001 through to 34 8170092 Model PA 34 220T aircraft S N 34 8133001 through to 34 8633031 and 3433001 through to 3433088 This AD supersedes DCA PA34 11C and DCA PA34 19 to combine the actions required in those ADs No action required for those aircraft in compliance with DCA PA34 11C and DCA PA34 19 To prevent the forward baggage compartment door from opening in flight accomplish the following 1 For model PA 34 200 aircraft S N 34 7250001 through to 34 7450220 and model PA 34 200T aircraft S N 34 7570001 through to 34 7970075 34 7970077 through to 34 7970105 34 7970107 through to 34 7970109 34 7970111 34 7970113 through to 34 7970117 34 7970120 34 7970121 34 7970123 through to 34 7970135 34 7970137 34 7970141 34 7970143 34 7970145 and 34 7970164 Modify the forward baggage door per the instructions in part
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