75-16-20: Propeller Pitch Control Lever
FAA order 75-16-20 is an airworthiness directive in force since August 12, 1975. The FAA's subject line: Propeller Pitch Control Lever. It names Mitsubishi MU-2: about 177 aircraft on the U.S. register today, though an order usually covers particular versions or serial numbers rather than every one. System: propeller.
What it applies to as the FAA lists it
- Kind of product
- Aircraft
- Makes
- Mitsubishi Heavy Industries, Ltd.
- Models
- MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-30, MU-2B-35, MU-2B-36
- On this site
- Mitsubishi MU-2 177 registered
Dates and paperwork
- In force since
- August 12, 1975
- Docket
- Unknown
- Replaced by
- 2020-26-14
- Status
- Historical
- The FAA's document
- Read the order on the FAA's site
The order itself the regulatory text, as published
Show the full text (2,073 characters)
75-16-20\tMITSUBISHI HEAVY INDUSTRIES, LIMITED: Amendment 39-2294. Applies to Mitsubishi Model MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B- 26, MU-2B-30, MU-2B-35, and MU-2B-36 airplanes certificated in all categories. \n\tCompliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished within the last 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection. \n\tTo prevent possible separation of the control lever on the engine propeller pitch control unit, inspect the propeller pitch control lever, Mitsubishi P/N 022A-43111, P/N 022A-43111-3, or P/N 867304-1 in accordance with paragraph (a) or (b) of this AD, as applicable. \n\t(a)\tFor airplanes with AN3H5A bolt or MS24673-3 bolt installed in a threaded propeller pitch control lever, accomplish the following: \n\t\t(1)\tRemove safety wire and loosen bolt. \n\t\t(2)\tEnsure that the propeller pitch control leveris mounted securely on the shaft. \n\t\t(3)\tRetorque the AN 3H5A bolt to 20-25 inch pounds or the MS24673-3 bolt to 25-30 inch pounds, as applicable, and install safety wire. \n\t\t(4)\tEnsure that the power management system is properly rigged in accordance with Section VI of the Garrett-Airesearch Turboprop Engine Series 331 Maintenance Manual or an FAA-approved equivalent. \n\t(b)\tFor airplanes with AN3-6A bolt and NAS679C3W nut installed in an unthreaded propeller pitch control lever, accomplish the following: \n\t\t(1)\tLoosen the AN3-6A bolt. \n\t\t(2)\tEnsure that the propeller pitch control lever is mounted securely on the shaft. \n\t\t(3)\tRetorque the AN3-6A bolt to 20-25 inch pounds. \n\t\t(4)\tEnsure that the power management system is properly rigged in accordance with Section VI of the Garrett-Airesearch Turboprop Engine Series 331 Maintenance Manual or an FAA-approved equivalent. \n\t(Mitsubishi MU-2 Service Bulletin No. 168, dated April 18, 1975, refers to this same subject). \n\tThis amendment becomes effective August 12, 1975.
Related safety bulletins advice on the same designs, not orders
2019-06-10CE-19-09 · Wing Miscellaneous Structure
2012-06-12CE-12-33 · Landing Gear Retraction/Extension System, Nose Landing Gear
2004-09-10CE-04-84 ·
2003-08-13CE-03-49 ·
2003-04-09CE-03-34 ·
Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of October 7, 2026. Connections as data: /graph/directive/75-16-20.json · aircraft systems.