AIRWORTHINESS DIRECTIVES FINAL RULES: 78-16-06

CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3275

AD NUMBER:   78-16-06

SUBJECT HEADING:   Airworthiness Directives; BEECH Models B19, C23, B24R, and C24R Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective August 14, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
78-16-06 BEECH: Amendment 39-3275. Applies to the following models and serial number airplanes certificated in all categories:
ModelSerial Numbers
B19MB-558 through MB-886
C23M-1413, M-1414, M-1416 through M-1418, M-1420 through M-1422, M-1424 through M-1438, M-1440 through M-1446, M-1448 through M-2009, M-2011 through M-2015, and M-2017 through M-2020.
B24RMC-151 through MC-448, MC-450, and MC-451.
C24RMC-449, MC-452 through MC-559, MC-561 through MC-563, MC-565 through MC-568 and MC-571.

COMPLIANCE: Required as indicated unless already accomplished.

To assure continued structural integrity of the rod between the stabilator trim tab actuator and the trim tab, within the next 25 hours time-in-service after the effective date of this AD, accomplish the following:

A) Visually inspect both ends of the stabilator trim tab actuator rod for proper rivet location, security of rivets and security of clevis fittings and rework if necessary, all in accordance with Beechcraft Service Instructions Number 0994 or later approved revisions.

B) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.

This amendment becomes effective on August 14, 1978.

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