AD 80-17-03

80-17-03 MOONEY: Amendment 39-3868. Applies to Model M20J airplanes Serial Numbers 24-0084, 24-0378 through 24-0906, 24-0908 through 24-0925, 24-0927 through 24- 0942, and 24-0946 (Airworthiness Directive Docket No. 80-ASW-3).

COMPLIANCE: Required as indicated unless already accomplished. To prevent total loss of engine oil, accomplish the following:

(a) Before further flight, unless already accomplished, remove the top cowl and inspect the positioning of the Rochester Model 3060-18 oil pressure transducer and the condition of the two 45-degree elbows as follows:

(1) Clean the oil pressure transducer fitting and the two 45-degree fittings with an oil soluble solvent.

(2) Inspect the Rochester Model 3060-18 oil pressure transducer for any evidence of contact with the engine mount. If damage is present, remove and replace it before verifying the clearance outlined in paragraph (a)(3).

(3) Verify a minimum of 0.40 inch clearance between the Rochester Model 3060-18 oil pressure transducer body and the upper right hand engine mount ring and between the Rochester Model 3060-18 oil pressure transducer and the two 45-degree elbow fittings and the engine mount tube. If any clearance is less than 0.40 inch, rotate the oil pressure transducer and its fittings to obtain this minimum clearance.

NOTE: Measure the 0.40 inch in an arc perpendicular to the crankshaft centerline. When this clearance exists the oil pressure transducer is almost contacting the vacuum pump body.

(4) Start and operate the engine until it is warm enough to respond smoothly to throttle changes (monitor oil temperature and cylinder head temperature gauges to maintain temperatures within limits), then stop the engine.

(5) Inspect the oil pressure transducer and its fittings for any signs of oil leakage.

(6) If any signs of oil leakage are detected, comply with paragraph (b) of this AD before further flight.

(b) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, modify the mounting provisions of the oil pressure transducer as follows:

(1) Remove the top cowl.

(2) Disconnect the wire from the oil pressure transducer, P/N 3060-18, and remove the transducer from the 45-degree fitting; retain for reinstallation.

(3) Remove the 45-degree fitting which was attached to the transducer. Leave the 45-degree fitting installed in the engine case port.

(4) Connect an AN 816-3 adapter to this 45-degree fitting.

(5) Connect the flex hose, P/N S94B90145, to this adapter and the other end, 1/8 inch pipe thread, to the transducer; use Tite Seal on all pipe threads. Position hose and fittings to obtain a clearance of .20 inch between hose socket and vacuum pump housing.

(6) Route the transducer and hose under the upper right hand engine mount tubes and secure the upper outboard tube with an AN742D25 and a MS21919DG8 clamp and an AN3-5A bolt, two AN960-10 washers and an AN363-1032 nut; the smaller clamp, MS21919DG8, clamps around the engine mount tube and the larger clamp, AN742D25, clamps around the transducer body as shown in Figure 1.

(7) Connect the ground wire, Wire No. 21DH04C20, under the bolt head holding the clamps together and to the landing light ground located on the firewall.

(8) Secure the hose to the engine mount with TY-RAP, MS3367-1 ensuring clearance between adjacent components.

(9) Reconnect the oil pressure gauge wire to the transducer connection post.

(10) Run the engine and check for oil leaks at the fittings connecting the flex hose and the engine and the flex hose and the oil pressure transducer. If leaks are noted, correct this situation before proceeding. Check the operation of the oil pressure gauge.

NOTE: Secure bottom cowling or remove prior to engine run.

(11) Replace cowling and secure all connections.

NOTE: Mooney Service Bulletin No. M20-221, "Oil PressureTransducer Installation Modification," pertains to this same subject.

(c) Special flight permits may be issued in accordance with FAR 21.197 and FAR 21.199 to fly airplanes to a base where this AD can be accomplished.

(d) Any alternate equivalent method of compliance with this airworthiness directive must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration.

This amendment supersedes Amendment 39-3725 (45 FR 20780) AD 80-07-12.

This amendment becomes effective August 18, 1980.

AD 80-17-03 FIGURE 1