AD 2006-18-12

Required as indicated, unless accomplished previously.

To prevent false warning indications to the flightcrew from the hot detection system of the tail pipe harness of the engine nacelles due to discrepancies of the harness, which could result in an unnecessary aborted takeoff on the ground or in-flight engine shutdowns, accomplish the following:

Within 12 months after the effective date of this AD: Modify the hot detection system of the tail pipe harness of the engine nacelles (including a general visual inspection of the heat shrink sleeve, thixotropic sealant, and connectors for damage and/or corrosion, and all applicable repairs), by doing all the actions specified in the Accomplishment Instructions of Saab Service Bulletin 340-26-030, Revision 01, dated November 14, 2003. All applicable repairs must be done before further flight in accordance with the service bulletin. Repeat the general visual inspection thereafter at intervals not to exceed 12 months.

Note 1: For the purposes of this AD, a general visual inspection is defined as: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”

(b) Accomplishing the modification/repetitive inspections specified in Saab Service Bulletin 340-26-030, dated October 28, 2002; or Saab Service Bulletins 340-26-018, Revision 02, and 340-26-029, both dated October 28, 2002; before the effective date of this AD, is considered acceptable for compliance with the modification required by paragraph (a) of this AD.

Within 30 days after any false warning indication to the flightcrew from the hot detection system of the tail pipe harness of the engine nacelles occurs: Submit a report containing the information specified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD to the Swedish Civil Aviation Authority (Luftfartsstyrelsen)—Attn: Mr. Christer Sundqvist, SAAB 340 Certification Manager, SE-601 79, Norrköping, Sweden. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.

(1) The date and time, weather conditions, and phase of flight of the warning.

(2) The action taken by the flightcrew to address the warning (aborted takeoff, high speed/high energy abort requiring inspection, return for landing, in-flight diversion, declared emergency, air traffic control (ATC) priority handling requested or given, or engine shutdown).

(3) The action taken by maintenance to address/correct the warning.

(4) Time-in-service on the airplane since the last inspection accomplished in accordance with paragraph (a) of this AD.