AD 86-24-10 ACTIVE

86-24-10 BRITISH AEROSPACE, PLC, Aircraft Group, Civil Division-Prestwick: Amendment 39-5480. Applies to Jetstream Model 3101 (including 3100) (all serial numbers) airplanes certificated in any category.

Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished.

To prevent engine flameout when in or departing an icing environment, accomplish the following:

(a) Revise the airplane Pilot's Operating Handbook and Airplane Flight Manual (POH/AFM) by inserting Appendix 1 of this AD in the "LIMITATIONS" section of the POH/AFM. Appendix 1 procedures supersede any other POH/AFM procedures which may be contradictory.

(b) The requirements of paragraph (a) of this AD are no longer required when the airplane is modified by the addition of an FAA approved automatic-relite ignition system.

NOTE: Automatic-relite ignition is a system which automatically energizes engine ignition without pilot action when engine RPM or torque decays below a specified level, and deenergizes engine ignition when RPM or torque exceeds the specified level. It is not synonymous with CONTINUOUS IGNITION.

(c) The requirements of paragraph (a) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173.

(d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(e) An equivalent method of compliance with this AD, if used, must be approved by contacting the Manager, Brussels Certification Office, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, 1000 Brussels, Belgium; Telephone 513.38.30, extension 2710/2711.

All persons affected by this AD may obtain copies of the document referred to herein upon request to GTEC, Post Office Box 5217, Phoenix, Arizona 85010; or British Aerospace, Engineering Department, Post Office Box 17414, Dulles International Airport, Washington, D.C. 20041; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment becomes effective on December 15, 1986.

APPENDIX 1
Supplement to the POH/AFM
BAe Model 3101 Airplanes

"The ENGINE ICE PROTECTION switch shall be selected to ANTI-ICE/IGN during all operations in actual or potential icing conditions described herein:

(1) During takeoff and climb out in actual or potential icing conditions.

*(2) When ice is visible on, or shedding from propeller(s), spinner(s), or leading edge(s).

(3) Immediately, any time engine flameout occurs as a possible result of ice ingestion.

(4) During approach and landing while in or shortly following flight in actual or potential icing conditions.

*NOTE: If icing conditions are entered in flight without the engine anti-icing system having been selected, switch one ENGINE system to ANTI-ICE/IGN position. If the engine runs satisfactorily, switch the second ENGINE system to the ANTI-ICE/IGN position and check that the second engine continues to run satisfactorily. CAUTION

Flight in actual or potential icing conditions will be limited by duty cycle of the ignition system. Ignition system time limits must be observed to prevent exceeding duty cycle times. Operator should verify these limits for his particular installation.

"Potential icing conditions in precipitation or visible meteorological conditions:

(1) Begin when the OAT is plus 5 degrees C (plus 41 degrees F) or colder, or

(2) End when the OAT is plus 10 degrees C (plus 50 degrees F) or warmer."

The procedures and conditions described in this appendix supersede any other POH/AFM procedures and conditions which may be contradictory.