85-11-07 R1 CESSNA: Amendment 39-5115. Applies to Models P210N, P210R (Serial numbers P21000001 through and including P21000855), and T210R (Serial numbers 21064898 through and including 21064929) airplanes, certificated in any category.
Compliance: Required as indicated, unless already accomplished.
To prevent possible separation of the turbocharger oil reservoir outlet fitting and subsequent rapid loss of engine lubricating oil, accomplish the following:
(a) Prior to further flight:
(1) Remove the right side engine cowling to the extent necessary to examine the turbocharger oil reservoir.
(2) Visually inspect using a strong light the top oil outlet fitting for cracks in the vicinity of the weld securing the fitting to the upper surface of the turbocharger oil reservoir.
NOTE: Cracking of the turbocharger oil reservoir outlet fitting may not be evidenced by an oil leak in the vicinity of the oil reservoir installation. Therefore, inspection of the reservoir will depend upon careful cleaning in addition to the use of a strong light.
(3) If no cracks are detected in the outlet fitting of the turbocharger oil reservoir, reinspect this area at each additional 25 hours time-in-service thereafter, or in the alternative, replace the turbocharger oil reservoir as follows:
(A) For Model P210N (serial numbers P21000001 through P21000834) airplanes remove the existing reservoir and install a Cessna Part Number 2150106- 32 reservoir in accordance with the installation procedures contained in Paragraphs (c)(1) through (c)(6) of this AD.
(B) For Model P210R (serial numbers P21000835 through and including P21000855), and T210R (serial numbers 21064898 through and including 21064929) airplanes remove the existing reservoir and install a Cessna Part Number 2150106-33 reservoir in accordance with the installation procedures contained in Paragraphs (c)(1) through (c)(6) of this AD.
(b) The repetitive inspections requiredby Paragraph (a) (3) of this AD may be discontinued when the modification in Paragraph (a) (3) (A) or Paragraph (a) (3) (B) of this AD is accomplished.
(c) If any cracks are detected in the outlet fitting in accomplishing Paragraph (a) (2) of this AD, prior to further flight, remove the existing turbocharger oil reservoir and install a Cessna Part Number 2150106-32 reservoir (for Model P210N serial numbers P21000001 through P21000834) or Part Number 2150106-33 reservoir (for Model P210R serial numbers P21000835 through and including P21000855) and Model T210R, (serial numbers 21064898 through and including 21064929) airplanes available from Cessna Aircraft Company using the following procedure:
(1) Install the check valve with the arrow pointing away from the oil reservoir outlet fitting.
(2) Use a wrench on the reservoir fitting to isolate the torque when tightening the check valve.
(3) Attach the breather vent line.
(4) Mount the rubber flexible hanger to the firewall and reservoir.
(5) Initially secure the oil inlet and outlet lines by hand. Then use a wrench on the oil reservoir inlet fitting and the check valve fitting to isolate the effects of tightening the oil scavenge hoses. Tighten the oil scavenge hoses to the turbocharger oil reservoir.
(6) Run the engine to check for oil leaks and eliminate any leaks prior to returning the airplane to service.
(d) An equivalent method of compliance may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209.
Cessna Single Engine Service Bulletin SE85-11, dated June 7, 1985, covers the subject matter of this AD.
This amendment becomes effective on August 9, 1985, to all persons except those to whom it has already been made effective by priority letter from the FAA dated June 6, 1985, and is identified as AD 85-11-07.