AIRWORTHINESS DIRECTIVE

CAA-AD-032/2001

Date of issue: April 17, 2001

HELICOPTER – SOLOY ENGINE RPM SENSOR

Applicability: Bell Helicopter Textron Canada Model 206B and Series 206L helicopters, equipped with Allison 250-C20R engine and Soloy engine power-out warning sensors, part number 206-075-545-001, in accordance with Supplemental Type Certificate (STC) SH 95-46 (FAA STC SH4l79 NM, applicable to Model 206B) and SH 95-45 (FAA STC SH4169NM, applicable to Model 206L).

Effective date: April 27, 2001.

Compliance : Required as indicated in TC AD CF-2001-13.

Remarks:. The compliance of this AD must be recorded in Aircraft Logbook, where applicable the requirements of this AD must be integrated into Aircraft Technical Documentation. Address inquiries concerning this AD to: Civil Aviation Authority, Airworthiness Division, Ruzyne Airport, 160 08 Prague 6, Czech Republic, tel: 420 2 33320922, fax: 420 2 20562270

Ing. Pavel MATOUŠEK
Director of Airworthiness Division
CAA CZ

No.: TC AD CF-2001-13

Subject: Bell 206B and 206L-Soloy Engine RPM Sensor

Effective: 27 ApriI2001.

Replacement: Supersedes FAA Airworthiness Directive (AD) 91-23-15.

Applicability: Bell Helicopter Textron Canada Model 206B and Series 206L helicopters, equipped with Allison 250-C20R engine and Soloy engine power-out warning sensors, part number 206-075-545-001, in accordance with Supplemental Type Certificate (STC) SH 95-46 (FAA STC SH4l79 NM, applicable to Model 206B) and SH 95-45 (FAA STC SH4169NM, applicable to Model 206L).

Compliance: Within 15 days after the effective date of this AD, unless already accomplished.

Background: FAA AD 95-24-06, which superseded FAA AD 91-23-15, mandated the addition of a warning and a note to the Rotorcraft Flight Manual to alert the pilot of a potential false engine-out warning from the above-noted Soloy sensor when practicing autorotations. Because AD 95-24-06 was issued after the date of transfer of Bell 206 design responsibility to Canada, it was not applicable outside the US. The present Transport Canada AD mandates the same requirements as FAA AD 95-24-06. The improved sensor P/N 680-2551-1 replaces the original sensor P/N 206-075-545-001.

Corrective Actions: Revise the Limitations section of the applicable approved STC Rotorcraft Flight Manual Supplement by adding the following Warning statement and Note:

WARNING: For aircraft with an engine-out sensor other than P/N 680-2551-1 only. To prevent false engine-out signals, the following procedure must be followed during practice auto-rotations. When entering a practice auto-rotation, avoid a pausing or creeping movement of any throttle decrease or increase between full open and idle. If movement is not made at a firm and continuous rate, N, RPM undershoot and/or oscillation may occur causing a momentary false engine-out warning light and audio indication.

NOTE: Ensure N1, RPM idle speed is set at 62-64%.”

Authorization:

For Minister of Transport

B Goyaniuk

Chief, Continuing Airworthiness

Contact: Mr. Luc Deniger, Continuing Airworthiness, Ottawa telephone (613) 952-5385, facsimile (613) 996-9178 or e-mail denigel@tc.gc.ca or any Transport Canada Centre.