Federal Register of Legislation
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 18 Series Aeroplanes
AD/BEECH 18/21 Main Landing Gear Walking Beam Upper Attach Bolt - Inspection and Replacement
11/81
Applicability: All models C-45G, TC-45G, C-45H, TC-45H, TC-45J (SNB-5) RC-45J (SNB-5P), D18C, D18S, E18S-9700, G18S, H18, JRB-3N, 3NM and 3TM fitted with Volpar tricycle landing gear.
Requirement: 1. Visually inspect the main landing gear walking beam upper attach bolt P/No. AN 179-46A for integrity and adequate installation.
2. Remove AN 179-46A bolt and associated hardware and install NAS 149-80 bolt and associated hardware as specified in "Description of Change" section of Volpar Inc. SB No. 22 dated 1 June 1981.
3. Visually inspect bolt P/No. NAS 149-80 installation for Integrity and replace with like serviceable part as necessary.
Note: FAA AD 81-18-07 Amdt. 39-4204 refers.
Compliance: 1. Within 10 hours time in service after 25 September 1981.
2. Within 200 hours time in service after 25 September 1981.
3. At intervals not to exceed 3000 hours time in service.
Background: Failure of the MLG walking beam upper attach bolt may occur in normal service.
Federal Register of Legislative Instruments F2006B03620
We try to embed the page this law was scraped from. If the site blocks framing, you still get the link and a local excerpt.
Last checked with source on —
Checking whether the official page can be embedded…
Plain-English simplify of this law: a short summary, key points, and both sides of the argument. Generated on first view via Replicate, then cached. Vote on what helps your study.
No study brief is cached for this law yet. Sign up to generate a plain-English brief.
Sign up to generate