AD 86-24-07 Engine Controls Installation
January 7, 1987
This AD applies to the 150C-M, A150K-M, 152, and A152.
These airplanes were equipped with ball type rod ends on the engine controls.
To prevent engine power interruption due to the engine control(s) becoming detached the engine controls must be modified by installing a castellated nut and cotter pin.
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