AD 87-07-09

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AD Number:
87-07-09
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; PIPER AIRCRAFT CORPORATION TED SMITH AEROSTAR) Models PA-60-600, PA-60-601...Show more
Subject:
Exhaust System Components
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/15/1987
Make:
Aerostar Aircraft Corporation
Model:
PA-60-600 (Aerostar 600) | PA-60-601 (Aerostar 601) | PA-60-601P (Aerostar 601P) | PA-60-602P (Aeros...Show more
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 87-07-09
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5600

AD NUMBER:   87-07-09

SUBJECT HEADING:   Airworthiness Directives; PIPER AIRCRAFT CORPORATION TED SMITH AEROSTAR) Models PA-60-600, PA-60-601, PA-60-601P, PA-60-602P and PA-60-700P Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 15, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
87-07-09 PIPER AIRCRAFT CORPORATION TED SMITH AEROSTAR): Amendment 39-5600. Applies to the following models and serial numbers of airplanes certificated in any category:

MODEL	SERIAL NUMBERS AFFECTED
PA-60-600 (Aerostar 600)	60-0001-003 through 60-0933-8161262
PA-60-601 (Aerostar 601)	61-0001-004 through 61-0880-8162157
PA-60-601P (Aerostar 601P)	61P-0157-001 through 61P-0860-8163455
PA-60-602P (Aerostar 602P)	62P-0750-8165001 and 62P-0861-8165002 through
62P-0932-8165055 and 60-8265001 through 60- 8365021
PA-60-700P (Aerostar 700P)	60-8423001 through 60-8423025.

Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished.

To prevent failed exhaust system components, accomplish the following on each engine:

(a) For affected Model PA-60-600 airplanes, remove the exhaust system components by accomplishing the following steps:

(1) Remove engine cowling.

(2) Remove exhaust stack support clamp from stack.

(3) Disconnect all stack flanges and remove complete exhaust stack assembly from each side.

(b) For affected Models PA-60-601, -601P, -602P, and -700P airplanes, remove the exhaust system components by accomplishing the following steps:

(1) Remove engine cowling.

(2) Loosen clamp on turbocharger exhaust port and slide rear section of exhaust stack aft and out.

(3) Disconnect waste gate control linkage and remove clamp attaching turbocharger waste gate.

(4) Slide waste gate section aft and out.

(5) Loosen balance tube end and center clamps, and compress balance tube.

(6) Disconnect all stack flanges and remove forward section of exhaust stack from each side.

(c) For all affected airplanes, visually inspect all exhaust system components by accomplishing the following:

(1) Clean and inspect all welds for cracks and pin holes, using a dye penetrant procedure.

(2) Inspect clamps, clamp bolts, and supports for condition and security of attachment.

(3) Inspect slip joints for signs of leaks and/or binding.

(4) Inspect stack flange mating surfaces for cracks or burns.

(5) Inspect turbocharger mounting flange on waste gate for cracks or burns.

(6) Rotate waste gate control level to insure proper operation.

(7) Inspect gaskets for signs of leaks. Discard gaskets at each disassembly.

(d) For all affected airplanes, inspect using dye penetrant procedures, the turbocharger attachment flange on aft section exhaust pipe for cracks, especially in the welds.

(e) Prior to further flight, replace all unserviceable parts including all used gaskets.

(f) For affected Model PA-60-600 airplanes, install the exhaust system by accomplishing the following steps:

(1) Prior to reassembly, clean up all slip joints and apply Fel-Pro antiseize lubricant (Type C5-A), Piper Part Number 912-012, to exhaust pipes at slip joints.

(2) Slide forward and aft sections together. Replace parts that do not assemble freely without binding.

(3) Place new flange gaskets into position and place exhaust system onto cylinder studs at exhaust ports. Install flange nuts loosely.

(4) Partially tighten all nuts. Never fully tighten any part of the exhaust system before proceeding to another part on the same side of the engine.

(5) Inspect slip joint after stacks are installed to assure proper alignment and freedom from binding when flange nuts are tightened.

(6) Tighten each part on one side of the engine uniformly until a torque of 205-215 inch pounds has been applied.

(7) Install exhaust stack support clamp onto stack, and adjust support rod ends so that clamp can be moved along stack by hand. Distance between stack and tunnel surface should be .50 inch minimum to 1.60 inch maximum on left stack; .75 inch minimum to 1.60 inch maximum on right stack. Replace parts which do not fall within this range.

(8) Start and run engine in accordance with the appropriate flight manual, shut down engine and check for leaks and correct as required.

(9) Install cowling.

(g) For affected Models PA-60-601, -601P, -602P, and -700P airplanes, install the exhaust system by accomplishing the following:

(1) Prior to reassembly, clean all slip joints and apply Fel-Pro antiseize lubricant (Type C5-A), Piper Part Number 912-012, to exhaust pipes and waste gates at all slip joints.

(2) Slide first and second sections of exhaust stack together. Replace parts that do not assemble freely without binding.

(3) Position stack flanges and new gaskets onto exhaust ports. Install flange nuts loosely.

(4) Install V-clamp onto turbocharger waste gate flange with opening aft.

(5) Position new gasket on waste gate turbocharger exhaust port. Spread V- clamp on turbocharger waste gate flange and install waste gate onto exhaust pipe and turbocharger. Install clamp nut loosely.

(6) Install V-clamp and new gasket on turbocharger exhaust port. Spread V- clamp and install aft section of exhaust stack onto turbocharger and waste gate. Install clamp nut loosely.

(7) Install balance tube, insuring that ends extend into clamps beyond slits in tube ends, and install end clamp bolts loosely.

(8) Starting at the front of the engine and working aft, partially tighten all nuts. Never fully tighten any part of the exhaust system before proceeding to another part on the same side of the engine.

(9) Reinspect all joints after parts are installed to assure proper alignment and freedom from binding when nuts are fully tightened.

(10) Tighten each part on one side of the engine uniformly, starting at front of engine and working aft. Torque flange nuts to 205-215 inch pounds and V-clamp nuts to 45-50 inch pounds.

(11) After completing both sides of engine, tighten balance tube clamps.

(12) Reconnect and adjust waste gate control linkage per Aircraft Maintenance Manual.
(13) Start and warm engine in accordance with appropriate flight manual, shut down engine, check for evidence of leaks and correct as necessary. Retorque V- clamps to 45-50 inch pounds.

(14) Install cowling.

(h) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(i) An equivalent means of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia 30349.

All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960; or may examine the document(s) referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

NOTE: Piper Aircraft Corporation Service Bulletin No. 818, dated February 25, 1986, pertains to the subject addressed by this AD.

This amendment becomes effective on May 15, 1987.

FOOTER: