AD 86-24-07

86-24-07 CESSNA: Amendment 39-5475. Applies to the following model and serial number single-engine airplanes certificated in any category manufactured thru Model year 1978 equipped with ball type rod ends on the engine controls.

MODELS SERIAL NUMBERS 150C thru 150M S/N 15059701 thru 15079405 A150K thru A150M S/N A1500001 thru A1500734 152 S/N 15279406 thru 15282031 A152 S/N A1520735 thru A1520808 172D thru 172N S/N 17249545 thru 17271034 R172K S/N R1722000 thru R1722929 P172D S/N P17257120 thru P17257188 177 thru 177B S/N 17700001 thru 17702752 177RG S/N 177RG0001 thru 177RG1366 180F thru 180K S/N 18051184 thru 18053000 182F thru 182Q S/N 18254424 thru 18266590 R182 S/N R18200001 thru R18200583 185B thru 185E S/N 185-0513 thru 185-1599 A185E, A185F S/N 18501600 thru 18503683 188, A188 S/N 188-0001 thru 188-0572 A188A, 188B S/N 18800573 thru 18803296 A188B S/N 18800967T thru 18803296T 205, 205A S/N 205-0001 thru 205-0577 206, U206 S/N 206-0001 thru 206-0275 U206A thru U206G S/N U206-0276 thru U206-1444 TU206A thru TU206G S/N U20601445 thru U20604649 P206, P206A thru P206E S/N P206-0001 thru P206-0603 TP206A thru TP206E S/N P20600604 thru P20600647 207, 207A, T207, T207A S/N 20700001 thru 20700482 210C thru 210M and T210K thru T210M

S/N 21058086 thru 21062954 T210F thru T210J S/N T210-0001 thru T210-0454 P210N S/N P21000001 thru P21000150 F150F thru F150M S/N F150-0001 thru F150-0529 S/N F15000530 thru F15001428 FA150K, FA150L S/N FA1500001 thru FA1500120 FRA150L, FRA150M S/N FRA1500121 thru FRA1500336 F152 S/N F15201429 thru F15201528 FA152 S/N FA1520337 thru FA1520347 FP172 S/N FP172-0001 thru FP172-0003 F172D thru F172N S/N F172-0001 thru F172-0654 S/N F17200655 thru F17201749 FR172E thru FR172K S/N FR17200001 thru FR17200630 F177RG S/N F177RG0001 thru F177RG0177 F182P, F182Q S/N F18200001 thru F18200094 FR182 S/N FR18200001 thru FR18200020 R172E thru R172H S/N R172-0001 thru R172-0409 S/N R1720410 thru R1720625

Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished.

To prevent engine power interruption due to loss of attachment of the engine controls, accomplish the following:

(a) Modify the engine controls installation by installing a drilled steel bolt, AN3l0 type castellated nut and a steel cotter pin in accordance with Cessna Single-Engine Customer Care Service Information Letter SE79-6.

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

(c) An equivalent means of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209.

All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Cessna Aircraft Company, Customer Services, Post Office Box 1521, Wichita, Kansas 67201; or the FAA, Rules Docket, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment becomes effective on January 7, 1987.