Airworthiness Directives; Beech Model 35-33, 35-A33, 35-B33, 35-C33, E33, 35-C33A, E33A, E33C, 35, 35R, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35-TC, V35A, V35A-TC, 36, 95-55, 95-A55, 95-B55, 95-B55A, 95-C55, 95-C55A, D55, D55A, 56TC, 95, B95, B95A, D95A and E95 Airplanes
Beechcraft 56TC Baron · Type Certificate
Overview
This document is an Airworthiness Directive (AD) issued by the Federal Aviation Administration (FAA) concerning various Beech aircraft models, including the Beechcraft 56TC. The directive mandates inspections and potential replacements of magnesium elevator control fittings to prevent failures that could compromise safety. The AD specifies compliance timelines and procedures for determining the composition of the fittings, as well as actions to take if magnesium fittings are found. This document is crucial for operators and maintenance personnel of the affected Beech aircraft models to ensure continued airworthiness and compliance with safety regulations.
- The AD mandates inspections of magnesium elevator control fittings on Beechcraft 56TC within 100 hours TIS after March 24, 1989.
- If magnesium fittings are found, they must be inspected every 100 hours TIS for cracks.
- Cracked magnesium fittings must be replaced with aluminum fittings before further flight.
- Operators may use alternative compliance methods if approved by the FAA.
- This AD applies to multiple Beech aircraft models, ensuring comprehensive safety oversight.
Document
Source
Originally published by services.casa.gov.au. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Type Certificate
- Year
- 1989
- Pages
- 3
- File size
- 130 KB
- Publisher
- services.casa.gov.au
Common. Rarer than 2% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Beechcraft 56TC Baron.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the 56TC to your watchlist and track it in one place.
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In this document
Applicability
The AD applies to a wide range of Beech aircraft models, including the Beechcraft 56TC, with specific serial number ranges provided for each model. This ensures that all affected aircraft are identified and subject to the required inspections.
Compliance Requirements
Operators must determine the composition of the elevator control fittings within 100 hours of time-in-service after the effective date of the AD. If magnesium fittings are found, further actions must be taken, including visual inspections every 100 hours and replacement if cracks are detected.
Inspection Procedures
The document outlines the inspection procedures for the magnesium elevator control fittings, referencing Beech Service Bulletin No. 2242. Operators are required to visually inspect the fittings for cracks and replace any cracked magnesium fittings with aluminum fittings.
Alternative Compliance
The AD allows for an equivalent means of compliance if approved by the FAA, providing flexibility for operators to meet safety requirements through alternative methods.
Effective Date
This Airworthiness Directive became effective on March 24, 1989, and compliance is required as indicated unless previously accomplished.
Safety notes
- Failure to comply with the AD may result in unsafe flight conditions due to potential elevator control fitting failures.
- Operators must ensure that inspections are performed within the specified time frames to maintain airworthiness.
Full document text
RGL Home Airworthiness Directive Federal Register Information Header Information DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Amendment 39-6144; AD 89-05-02 Airworthiness Directives; Beech Model 35-33, 35-A33, 35-B33, 35-C33, E33, 35-C33A, E33A, E33C, 35, 35R, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35-TC, V35A, V35A-TC, 36, 95-55, 95-A55, 95-B55, 95-B55A, 95- C55, 95-C55A, D55, D55A, 56TC, 95, B95, B95A, D95A and E95 Airplanes PDF Copy (If Available): Preamble Information AGENCY: Federal Aviation Administration, DOT DATES: Effective March 24, 1989. Regulatory Information 89-05-02 BEECH: Amendment 39-6144. Applicability: The airplanes listed below, certificated in any category: MODELS SERIAL NUMBERS 35-33, 35-A33, 35-B33, 35-C33, E33 CD-1 through CD-1234 35-C33A, E33A CE-1 through CE-289 E33C CJ-1 through CJ-25 35, 35R, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35-TC, V35A, V35A-TC D-1 through D-9068, D-15001 and D- 15002 36 E-1 through E-184 95-55, 95-A55, 95-B55, 95-B55A TC-1 through TC-1287 95-C55, 95-C55A, D55, D55A TE-1 through TE-767 56TC TG-2 through TG-83 95, B95, B95A, D95A, E95 TD-2 through TD-721 This AD also applies to any of the following military airplanes which have been modified for civil certification as described on the applicable Federal Aviation Administration Type Certificate Data Sheet or Aviation Specification: T34A, T34B (Commercial Model 45 Series) T42A (Commercial Model 95-B55B) NOTE: The magnesium fittings may have been installed as original equipment or as replacement spares. Compliance: Required as indicated, unless already accomplished. To prevent the failure of the magnesium elevator control fittings, accomplish the following: (a) Within 100 hours time-in-service (TIS) after the effective date of this AD, determine the composition of the elevator control fittings in accordance with the instructions contained in Beech Service Bulletin No. 2242, Revision 1, dated August 1988. (1) If the fittings are determined to be aluminum, no further action is required by this AD. (2) If the fittings are determined to be magnesium, accomplish the actions specified below. (b) At the time of the inspection per paragraph (a), and every 100 hours TIS thereafter, visually inspect each magnesium elevator control fitting for cracks in accordance with the above referenced Service Bulletin. (c) If any fitting is found to be cracked, prior to further flight replace the cracked fitting with an aluminum fitting as described in the above referenced Service Bulletin. (d) The above inspections are no longer required when aluminum fittings have been installed on both elevators. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid- Continent Airport, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beechcraft Aero and Aviation Centers; Beech Aircraft Corporation, Commercial Service, Dept. 52, P.O. Box 85, Wichita, Kansas 67201-0085, or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6144, AD 89-05-02) becomes effective on March 24, 1989. Footer Information Comments FAA.gov Home | Privacy Policy | Web Policies & Notices | Contact Us | Help Readers & Viewers: PDF Reader | MS Word Viewer | MS PowerPoint Viewer | MS Excel Viewer | WinZip
What's in the Beechcraft 56TC Baron TCDS
A Type Certificate Data Sheet (TCDS) is the FAA's record of what an aircraft type was approved as. It is the source of truth for weights, seating, fuel and the rules the design was certified against. Expand any line to see what it means.