Piper Tomahawk AD List

This is Page 2. - 82-27-08 to 93-19-04
Go to Page 3. - 95-03-02 to 98-03-16



 
	82-27-08 Forward Fin Spar S/N 38-78A0001 thru 38-82A0122.
	To prevent possible failure of the fin and associated fuselage structure because of fatigue damage.
	(a) On S/N 38-78A0001 through 38-80A0198
	  (1) On airplanes which do not have Kit P/N 764427 on an undamaged forward fin spar.
	      Before 325 hours and then at intervals not over 100 hours thereafter.
	    (i) Inspect the forward surface of the forward fin spar web P/N 77601-03 in the area of the forward fin spar
	        attach fitting P/N 77553-05 for cracks using a dye penetrant method. Remove two forward fin attach bolts
	        and displace fin spar 1/8" laterally in each direction to increase visibility of spar area adjacent to
	        edge of attach fitting. Remove any scuff marks on spar by burnishing prior to applying dye penetrant.
	   (ii) Replace or repair forward fin spars having cracks exceeding 1/2" long with forward fin spar
	        P/N 77601-1 and Forward Fin Spar Modification Kit 764427. Replace or repair parts which have cracks less
	        than one-half inch within 25 hours.
	  (2) On airplanes without fuselage bulkhead assembly P/N 77553-06.
	      Before 325 hours and then at intervals not over 300 hours thereafter.
	    (i) Inspect the fuselage bulkhead assembly P/N 77553-02 at fuselage station 221.42, in the area of the
	        Forward Fin Spar Attach Plate P/N 77553-05, for cracks using a dye penetrant method or equivalent.
	        Access the aft side of the bulkhead by removing rudder and adjacent access door and to front side by
	        removing the luggage compartment rear partition. When using luggage compartment, provide a stand to
	        support the aft fuselage and provide a support board for the mechanic.
	   (ii) Repair or replace bulkheads having cracks exceeding 3/4" long with bulkhead assembly P/N 77553-06,
	        or equivalent part. Replace or repair parts which have cracks less than 3/4" long within 25 hours.
	  (3) On airplanes without Aft Vertical Fin Spar Assembly P/N 77601-16, Upper Rudder Hinge Shim P/N 85606-02,
	      and Fuselage Bulkhead Assembly P/N 85615-02, before 2500 hours and every 200 hours thereafter,
	    (i) Inspect Aft Vertical Fin Spar P/N 77601-02 for cracks as per SB 745, Part IV, by dye penetrant method or equal.
	   (ii) If cracked, repair or replace Aft Fin Spar P/N 77601-02 and Aft Fuselage Bulkhead Assembly P/N 77554-02,
	        with Aft Vertical Fin Spar Assembly P/N 77601-16, Upper Rudder Hinge Shim P/N 85606-02, and
	        Fuselage Bulkhead Assembly P/N 85615-02.
	  (4) Within 25 hours or at 3000 hours TT, whichever is later, and thereafter at intervals not over 3000 hours, replace
	      the Forward Fin Spar Attachment Plate P/N 77553-05 with a new part.

	(b) S/N 38-81A0001 thru 38-82A0101
	  (1) On airplanes without Kit 764421 installed, within 25 hours or upon reaching 3000 hours TT, whichever is later,
	      and at intervals not over 3000 hours, replace the Forward Fin Spar Attachment Plate P/N 77553-05 with a new part.
	  (2) On aircraft with Kit 764421 installed, within 25 hours or upon reaching 5000 hours TT, whichever is later, and at
	      intervals not over 5000 hours, replace the Forward Fin Spar Attachment Plate P/N 77553-05 with a new part.

	(c) S/N 38-82A0102 thru 38-82A0122
	  (1) Within 25 hours or upon reaching 5000 hours TT, whichever is later, and at intervals not over 5000 hours,
	      replace the Forward Fin Spar Attachment Plate P/N 77553-05 with a new part.

	NOTE: Retirement time for the Forward Fin Spar Attachment Plate P/N 77553-05 on S/N 38-82A0123 and higher is
	      contained in the Flight Manuals delivered with these airplanes. SB 710 and 745, of Oct 10,1982 refer to
	      this subject. This amendment supersedes AD 81-04-07.

	83-05-04 Landing Gear Bolts. See 90-19-03

	83-14-08 Flow Strips. S/N 38-78A0001 thru 79A0582.
	 Within the next 100 hours. To standardize and improve the stall characteristics.
	 (a) Install Flow Strip Kit 763-930.
	 (b) Replace the airspeed indicator with P/N 61906-02 or 61905-02, or alter the original
	     airspeed indicator markings to read as follows:
	   (1) Red radial 138 knots.
	   (2) Yellow arc from 110 to 138 knots.
	   (3) Green arc from 52 to 110 knots.
	   (4) White arc from 49 to 89 knots.
	     If the instrument is remarked, it must be done by a certificated and appropriately rated instrument repair station.
	 (c) Insert P/N 761-658, Revision 3, of Dec 18,1978, containing performance information applicable to airplanes with
	     Kit P/N 763-930 installed in the Pilot's Operating Handbook.
	  Piper SB 876 of April 12,1979, covers this AD.
    
	83-19-01 Vertical Fin Kit 764965. S/N 38-78A0001 thru 82A0122
	 To prevent possible failure of the fin and stabilizer attachment because of fatigue damage.
	 (a) Upon reaching 525 hours or bofore, and at intervals not over 100 hours thereafter.
	     Inspect and, if needed, repair or modify the Forward and Aft Fin Spars as per SB 763A of July 25,1983.
	 (b) The repetitive inspections required by this AD may be discontinued by the installation of Kit 764965.

	84-26-02 Air Inlet Filter
	 To prevent possible engine power loss by engine ingestion of fragments of a deteriorated induction air filter.
	 Within the next 100 hours or prior to the accumulation of 500 hours on the filter, whichever occurs later,
	 and thereafter at intervals not over 500 hours.
	 (a) Replace the air filter with a new filter that is FAA approved for the airplane installation.
	 (b) Within 100 hours replace any filter on which the time-in-service cannot be determined utilizing the airplane
	     maintenance records.
	 NOTE: This AD does not alter current maintenance procedures which require inspection of paper induction air filters
	 at 100 hours time-in-service and annual inspections and replacement as necessary based on filter condition.
	 This amendment becomes effective January 29, 1985.

	85-11-06 Control Wheel Shaft Bushing S/N 38-78A0001 thru 38-82A0122. Within the next 50 hours.
	  To prevent the loss of control.
	  (a) For S/N 38-78A000I through 79A1160.
	      Modify the control wheel shaft bushing in accordance with SB 661 of Aug.22,1979.
	  (b) For S/N 38-78A0001 through 82A0122.
	      Modify the elevator control travel as per SB 800 of Nov 19,1984.

	24 Aug 1990. (AD number unknown) Oil Pressure Line Fitting To reduce engine oil loss
	 in case of oil pressure line failure, replace the 90 degree fitting per Piper SB 936. If an optional
	 hour meter oil pressure switch is installed, inspect the Tee fitting and Nipple attaching the
	 Transducer and Switch as per the SB. If aluminum fittings are found, replace per the SB before
	  further flight. Compliance within the next 100 hours TIS. 

	90-19-03 Landing Gear Modification All serial numbers.
	  Within 100 hours, to preclude loosening of the landing gear attachments and possible gear separation.
	  (a) Modify the main landing gear as per SB 673B of Oct 2,1986.

	92-15-16 Marvel-Schebler Carburetors See 93-19-04

	93-05-06 Magneto/Start Switch & Solenoid Diode
	  To prevent failure of Mag/Start switch.
	 (a) Within 100 hours or at the next annual inspection, whichever is first, inspect the Mag/Start Switch
	  to detect wear and corrosion, and lubricate the switch, in accordance with ACS SB SB92-01 of Aug 15,1992.
	  If wear or corrosion is detected, replace the switch in accordance with the service bulletin.
	  Repeat this inspection and lubricate the Switch thereafter, at least every 2,000 hours.
	 (b) Inspect to see if a diode or other surge suppressor is installed on the Starter Solenoid.
	  If if there is none, install a Diode in accordance with ACS SB 92-01.

	93-18-03 Marvel-Schebler Carburetor Venturi See 98-01-06	

	93-19-04 Marvel Schebler Carburetor Float
	 M/S Model MA3, MA3A, MA3PA, MA3SPA, and MA4SPA carburetors installe on Lycoming 0-235 emgines.
	 To prevent a disruption of fuel flow to the engine, do the following:
	 (a) Prior to further flight, for carburetors repaired or rebuilt from Nov.1,1991, thru July 15,1992, do the following:
	  (1) Visually inspect the float for Consolidated Fuel Systems P/N CF 30-766 and remove the float if the
	      date "10 91" is stamped on the top of the float lever arm, and replace with a serviceable float.
	NOTE: CFS Mandatory Service Bulletin CF-1-92, Revision 1, dated July 6, 1992, gives a listing of those known
	carburetors repaired or rebuilt during the suspect time period.
	NOTE: Guidance on replacing floats is contained in either Precision Airmotive (Facet) Aircraft Carburetor Service
	Manual, dated September 1984, or CFS Carburetor Float Kit Installation Instructions, CF 666-915.
	  (2) Floats identified with Precision Airmotive P/N 30-766 with any date stamped on the float lever arm,
	      or CFS P/N CF 30-766 with dates 8 89, 12 89, 1 90, 2 90, 8 90, 10 90, 1 91, 2 91, 4 91, 4 92, or 7 92
	      stamped on the float lever arm do not need to be removed.
	  This amendment becomes effective on October 18, 1993. 
02-07-95 Textron MSB 518A Thermo By-Pass Valve Loose Nut 01-26-95 Textron MSB 522 O-235 Push Rod P/N 73806V & X. N/G Service Life Limits PIPER Information Manual Section 2.18 (a) Lower Longitudinal Trim Springs, drawing 37523 or 61916-2, 1500 hours. (b) Wing, drawing 77352 and associated structure, 11,000 hours maximum. (c) Steel Upper Rudder Hinge, drawing 77610-03, 5000 hours. (d) Fin Spar Attachment Plate, drawing 77553-05. S/N 78A0001 thru 80A0198. 3000 hours. S/N 81A0001 thru 82A0101 without Kit 764421 installed, 3000 hours. S/N 81A0001 thru 82A0101 with Kit 764421 installed, 5000 hours. S/N 82A0102 and up, 5000 hours. AUSTRALIA AD/PA-38/27 Wing Fatigue 3/98 Piper PA-38 Tomahawk Aeroplanes Applies to: All PA-38-112 aircraft. Requirement: Retire wing and associated structure. This includes the wing attachment fittings both in the wing and the fuselage. Compliance: Within 200 hrs time in service (TIS) after 26 February 1998 or at 11000 hrs TIS, whichever occurs last. Background: This AD mandates the Service Life Limit listed in the Maintenance Manual and the USA FAA Type Certificate Data Sheet. This AD is effective as of February 26,1998. Web site

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AOPA and other reports on the Tomahawk Stall/spin controversy
----- AOPA Air Safety Report Feb. 1997---- Follow-up article----- NTSB wants new Spin Tests

Search Tail Numbers------ FAA Regs - AD's etc.------ NTSB Accident Reports
Sport Flyer.com ------ Engine/Prop Info------ Aviation Weather------ AirSpace Class

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