AD 94-27111
Published 1994-11-02 · 24 models · 5,976 US-registered tails affected · Federal Register
Airworthiness Directives; Beech Aircraft Corporation 33, 35, and 36 Series Airplanes Federal Register ↗
Abstract
This document proposes to supersede Airworthiness Directive 92-08-07, which currently requires inspecting (one-time) the wing front spar carry-through frame structure for cracks on certain Beech 33, 35, and 36 series airplanes, and, if found cracked, repairing or reinforcing. The Federal Aviation Administration (FAA) has received 43 reports of wing front spar carry-through frame structure cracks on the affected airplanes during the inspection required by AD 92-08-07. The proposed action would make this one-time inspection repetitive. The actions specified by the proposed AD are intended to prevent spar carry-through structure failure, which could result in severe structural damage to the wing.
Applicability · by US fleet size
- BEECH F33A TCDS 3A15 978 tails
- BEECH V35B TCDS 3A15 913 tails
- BEECH S35 TCDS 3A15 459 tails
- BEECH V35 TCDS 3A15 425 tails
- BEECH V35A TCDS 3A15 321 tails
- BEECH P35 TCDS 3A15 319 tails
- BEECH B36TC TCDS 3A15 307 tails
- BEECH 35-B33 TCDS A-777TCDS 3A15 290 tails
- BEECH K35 TCDS 3A15 237 tails
- BEECH M35 TCDS 3A15 225 tails
- BEECH H35 TCDS 3A15 224 tails
- BEECH J35 TCDS 3A15 221 tails
- BEECH 35-C33 TCDS A-777TCDS 3A15 185 tails
- BEECH A36TC TCDS 3A15 173 tails
- BEECH N35 TCDS 3A15 167 tails
- BEECH 35-33 TCDS A-777TCDS 3A15 130 tails
- BEECH 35-C33A TCDS A-777TCDS 3A15 113 tails
- BEECH 35-A33 TCDS A-777TCDS 3A15 84 tails
- BEECH E33 TCDS 3A15 62 tails
- BEECH E33A TCDS 3A15 51 tails
- BEECH G33 TCDS 3A15 41 tails
- BEECH E33C TCDS 3A15 20 tails
- BEECH F33C TCDS 3A15 17 tails
- BEECH F33 TCDS 3A15 14 tails
Compliance instructions
Required actions, compliance times, parts/serial numbers and methods of compliance are in the Federal Register publication — not paraphrased here. Read AD on Federal Register ↗