Airworthiness Directive

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Federal Aviation Administration

14 CFR Part 39

Amendment 39-1478; AD 72-14-07

Airworthiness Directives; Piper Models PA-28-140, PA-28-150, PA-28-160, PA-28-180, PA-28-235, PA-28R-180, PA-28R-200, PA-32-260, PA-32-300, and PA-34-200
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AGENCY: Federal Aviation Administration, DOT

DATES: Effective July 7, 1972.

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72-14-07 PIPER: Amdt. 39-1478. Applies to the following airplanes certificated in all categories:
PA-28-140Serial Nos. 28-20001 thru 28-7225389
PA-28-150/-160/-180Serial Nos. 28-03 and 28-1 thru 28-7205256
PA-28-235Serial Nos. 28-10001 thru 28-7210018
PA-28R-180Serial Nos. 28R-30002 thru 28R-7130013
PA-28R-200Serial Nos. 28R-35001 thru 28-R-7235217
PA-32-260Serial Nos. 32-03, 32-04 and 32-1 thru 32-7200031
PA-32-300Serial Nos. 32-15, 32-21 and 32-40000 thru 32-7240103
PA-34-200Serial Nos. 34-E4 and 34-7250001 thru 34-7250242

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

To insure properly tightened bolts on the stabilator hinge attachment fittings, which are secured to the aft fuselage bulkhead, accomplish the following:

(a) Remove tail cone fairing and closeout panel from aft fuselage bulkhead to gain access to the twelve (12) fitting attachment nuts. There are six bolts and nuts per fitting.

(b) Inspect around bolt holes in bulkhead and fitting for cracks, deformation, or other damage.

(c) Torque nuts to a value of 35-40 inch pounds and reinstall closeout panel and tail cone fairing.

Piper Service Letter No. 614 pertains to this same subject.

This amendment becomes effective 7 July 1972.