Airworthiness directives › 2020-26-14
AD 2020-26-14 Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. Airplanes
Models named: MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-26A, MU-2B-30, MU-2B-35, MU-2B-36. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) Models MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-26A, MU-2B-30, MU-2B-35, MU-2B-36, MU-2B-36A, MU-2B-40, and MU-2B-60 airplanes, certificated in any category.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) For all airplanes except Model MU-2B and MU-2B-10 airplanes: Within 100 hours time-in-service (TIS) after the effective date of this AD or within 12 months after the effective date of this AD, whichever occurs first, modify the PPC lever linkage as specified in paragraphs (g)(1)(i) through (iii) of this AD, as applicable. (i) Replace the PPC lever clamping bolt in accordance with the Accomplishment Instructions, section 2, of Mitsubishi MU-2 Service Bulletin No. 106/76-004, dated February 24, 2016, or Mitsubishi MU-2 Service Bulletin No. 244, dated December 25, 2015, as applicable to your model airplane. (ii) For airplanes without a threaded hole in the splined end of the shouldered shaft of the PPC assembly, incorporate a threaded hole in accordance with the Accomplishment Instructions, paragraph 3.C.(3)(d) 2, of Honeywell International Inc. Service Bulletin TPE331-72-2190, Revision 0, dated December 21, 2011. (iii) Install a secondary retention feature in the threaded end of the PPC input shaft in accordance with the Accomplishment Instructions, section 2, of Mitsubishi MU-2 Service Recommendation No. 049/76-002, dated June 29, 2018, or Mitsubishi MU-2 Service Recommendation No. 080, dated June 29, 2018, as applicable to your model airplane. (2) For Model MU-2B and MU-2B-10 airplanes: Within 100 hours TIS after the effective date of this AD or within 12 months after the effective date of this AD, whichever occurs first, replace the PPC lever clamping bolt and install a secondary retention feature in the threaded end of the PPC input shaft using a method approved by the Manager of the Fort Worth ACO Branch, FAA. The Manager's approval letter must specifically refer to this AD.
Unsafe condition
This AD was prompted by propeller pitch control (PPC) lever linkages disconnecting at the engine. The FAA is issuing this AD to address the PPC lever linkage from disconnecting at the engine, which could lead to the inability to control the propeller pitch with the power lever in the cockpit and consequent loss of control of the engine power settings.
Affected ADs
This AD replaces AD 75-16-20, Amendment 39-2294 (40 FR 31751, July 29, 1975) (AD 75-16-20).
Read the original on the Federal Register →
You just looked this one up by hand
TrackAD holds all 12,278 of them and matches them against the aircraft you actually look after — airframe, engine, propeller and appliances in one pass — then works out what falls due and when.
- Bring your existing list in from a spreadsheet Paste the rows straight out of Excel. Headers like C/W Date and N/A are read for you.
- A copy that works when this does not One file. No internet, no login, no this software running. For the morning something has to be produced and the computer is not cooperating.
- $5 a month, or $50 a year Up to 50 aircraft on either.
Look round a real shop first Start free
The demonstration shop is eleven real aircraft with a year of work behind them. No account needed.
The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1