Airworthiness Directive

AD 2001-23-04 66 FR 57857 Active

Federal Aviation Administration · 14 CFR part 39

FR document
01-28333
Amendment
39-12501
Published
2001-11-19
Effective
2002-01-04
Models covered
1
Last live check
2026-10-02
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AD

2001-23-04

FR doc 01-28333 · 66 FR 57857

AD 2001-23-04Published 2001-11-19Effective 2002-01-04

FAA rule - 14 CFR 39

FAA rule. Compliance with an applicable AD is required under 14 CFR 39.7. Check its effective date, applicability, compliance times and current status.

Requires you to repetitively inspect the lower rudder hinge fitting for cracks.

Full official abstract

This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe Aerospatiale (SOCATA) Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. This AD requires you to repetitively inspect the lower rudder hinge fitting for cracks. This AD also requires you to repair any crack found in accordance with a repair scheme obtained from the manufacturer through the Federal Aviation Administration (FAA). This AD is the result mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect and correct fatigue cracks in the lower rudder hinge fitting. This condition could cause the lower rudder to detach from the control linkage with consequent loss of control of the airplane.

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All SOCATA TB (Tampico/Tobago/Trinidad) directives

Applies to 1 model in our index