Document ID: chunk:federal_register_of_legislation:F2006B02521:body:0:p1
Version: federal_register_of_legislation:F2006B02521
Segment Type: other
Provision Reference: 
Character Range: 12–3287

AIRWORTHINESS DIRECTIVE

 For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/AS 355/71 and issues the following AD under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

 Eurocopter AS 355 (Twin Ecureuil) Series Helicopters

 AD/AS 355/71
 Amdt 1

 Electrical Power System 11/2003

            Applicability: AS 355 helicopter versions E, F, F1, F2 and N, equipped for IFR flights, before embodiment of MOD 073019 or before compliance with Eurocopter AS 355 Alert Service Bulletin (ASB) No. 24.00.14, and equipped with the following part number electrical master boxes:

        48xGC01Yxxx or 49xGC01Yxxx

        Note 1: x in the part number indicates any digit.

              Requirement: 1. If not previously accomplished in accordance with AD/AS 355/55 or the original issue of this Directive, revise the Aircraft Flight Manual (AFM) as follows:

                  1. Insert the following into the Limitations Section, Operating Limitations, Electrical and Hydraulic Power Systems Limitations (Section 2.1.13):

                    Landing Lights
                    Do not use the landing light outside the landing and take-off phases.

                 b.        Insert the following into the Emergency Procedures Section, Systems Malfunction, Electrical Power Systems Failures (Section 3.2.5):

                    Loss of Electrical Power Generating Systems, Except for the Battery  Direct Battery Power (Indicated to the pilot by the equipment connected to the Bus Bars PP11, PP12, PP13, PP14, PP19 and PP20 - Refer to AFM Section 7.8)

                      -                                                                                                                     Apply the following procedure

                          * Limit the aircraft speed to 100 knots (reduce this value by 1 knot every 1000 ft) in order to minimise the risk of engine limit exceedence.

                          * Land as soon as possible

                          * Estimate the remaining flight time taking into account the last known fuel quantity and average fuel consumption of 200 kg per hour. The remaining flight time, starting from the loss of electrical power generating systems, shall not exceed the minimum value between the previously calculated flight time and the maximum flight duration using battery power, which is 45 minutes during the day and 30 minutes at night.

            These revisions may be accomplished by inserting a copy of this Directive into the AFM.

              2.         If not previously accomplished in accordance with AD/AS 355/55 or the original issue of this Directive, install a placard, in clear view of the pilot, with letters of at least 6 mm (¼ inch) high, stating:

                Do