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.

150C thru 150MS/N 15059701 thru 15079405
A150K thru A150MS/N A1500001 thru A1500734
152S/N 15279406 thru 15282031
A152S/N A1520735 thru A1520808
172D thru 172NS/N 17249545 thru 17271034
R172KS/N R1722000 thru R1722929
P172DS/N P17257120 thru P17257188
177 thru 177BS/N 17700001 thru 17702752
177RGS/N 177RG0001 thru 177RG1366
180F thru 180KS/N 18051184 thru 18053000
182F thru 182QS/N 18254424 thru 18266590
R182S/N R18200001 thru R18200583
185B thru 185ES/N 185-0513 thru 185-1599
A185E, A185FS/N 18501600 thru 18503683
188, A188S/N 188-0001 thru 188-0572
A188A, 188BS/N 18800573 thru 18803296
A188BS/N 18800967T thru 18803296T
205, 205AS/N 205-0001 thru 205-0577
206, U206S/N 206-0001 thru 206-0275
U206A thru U206GS/N U206-0276 thru U206-1444
TU206A thru TU206GS/N U20601445 thru U20604649
P206, P206A thru P206ES/N P206-0001 thru P206-0603
TP206A thru TP206ES/N P20600604 thru P20600647
207, 207A, T207, T207AS/N 20700001 thru 20700482
210C thru 210M and
T210K thru T210M
S/N 21058086 thru 21062954
T210F thru T210JS/N T210-0001 thru T210-0454
P210NS/N P21000001 thru P21000150
F150F thru F150MS/N F150-0001 thru F150-0529
S/N F15000530 thru F15001428
FA150K, FA150LS/N FA1500001 thru FA1500120
FRA150L, FRA150MS/N FRA1500121 thru FRA1500336
F152S/N F15201429 thru F15201528
FA152S/N FA1520337 thru FA1520347
FP172S/N FP172-0001 thru FP172-0003
F172D thru F172NS/N F172-0001 thru F172-0654
S/N F17200655 thru F17201749
FR172E thru FR172KS/N FR17200001 thru FR17200630
F177RGS/N F177RG0001 thru F177RG0177
F182P, F182QS/N F18200001 thru F18200094
FR182S/N FR18200001 thru FR18200020
R172E thru R172HS/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