AD/SA 315/13 Horizontal Stabiliser Spar (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(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 SA 315 (Lama) Series Helicopters

AD/SA 315/13 Horizontal Stabiliser Spar 13/2006

Applicability:

Model SA 315 B helicopters.

Requirement:

1.    STABILISERS PART NUMBER 315A-35-10-000-1

a.     Accomplishment of a visual inspection in accordance with paragraph 2.B(1) of Eurocopter SA 315 Service Bulletin (SB) No. 55.01 Revision 2, was required within 3 months after 14 December 1996.

If corrosion is detected inside the tube, other than in the half-shell area, replacement of the tube was required within 500 flight hours or by
31 December 1998, whichever occurred first.

b.    Compliance with paragraph 2.B(2) of SB No. 55.01 Revision 2, which corresponds to the embodiment of modifications 07.2215 (adding half shells on the spar tube) and 07.2214 (installation of the spar tube without play), was required by 1 March 1984, as mandated by DGAC AD 83-204-026(B), which has since been cancelled.

c.     Once compliance with Requirement 1.b. is confirmed, accomplish the following:

(i)    Visually check the installation of the half-shells and the horizontal stabiliser.

(ii)   Visually check the condition of the installation and lubricate the spar tube attachment bolts.

d.    For the horizontal stabilisers part number 315A35-10-000-1 on which modification 07.2215 has been embodied, the airworthiness aspects covered by DGAC AD 85-194-030(B) (effective 27 November 1985) which is superseded and replaced by DGAC AD 96-277-037(A) (this AD) remain applicable.  These aspects are as follows:

Confirm that there are no traces of marking on the spar tube and rework the stabiliser support fittings in accordance with paragraph C.1. of Eurocopter Service Bulletin (SB) No. 01.23.

e.     For horizontal stabilisers part number 315A35-10-000-1 on which modification 07.2215 has been embodied and which do not have the letter ”X” engraved on the identification plate in the official stamp area, the airworthiness aspects covered by DGAC AD 88-025-031(B) (effective
13 February 1988) which is superseded and replaced by DGAC AD
96-277-037(A) (this AD) remain applicable.  These aspects are as follows:

With a view to removing any traces of corrosion and improving the protective treatment at the half-shell-to-stabiliser tube centre section assembly points, the following measures were to have been applied at the 400 flight hour interval or by 13 February 1989, whichever occurred first.

Carry out the checks and any required reworking, return the assembly to airworthy condition and mark the letter “X” on the stabiliser in accordance with paragraph C.1. of Eurocopter Service Bulletin (SB) No. 01.25.

2.    STABILISERS PART NUMBER 315A35-10-000-2 and HIGHER DASH NUMBERS

a.     Accomplishment of a visual inspection in accordance with paragraph 2.B(1) of SB No. 55.01 Revision 2, was required within 3 months after
14 December 1996.

If corrosion is detected inside the tube, other than in the half-shell area, replacement of the tube was required within 500 flight hours or by
31 December 1998, whichever occurred first.

b.    A check, and if necessary, modification of the supports and the stabiliser was required by 14 June 1997 in accordance with paragraph 2.B.(2) of SB No. 55.01 Revision 2 (embodiment of modification 07.2215), provided that the instructions in paragraph 2.B.(3) of SB No. 55.01 Revision 2 were applied once within 8 days or 10 flight hours, whichever occurred first, from the effective date of DGAC AD 96-277-037(A) R1 dated 21 May 1997 (A check of the condition of the tube inside the area which is covered by the two half-shells.  If a crack is found, discard the tube).

c.     Once compliance with Requirement 2.b. is confirmed, accomplish the following:

(i)    Visually check the installation of the half-shells and the horizontal stabiliser.

(ii)   Visually check the condition of the installation and lubricate the spar tube attachment bolts.

d.    Embodiment of modification 07.2214 (installation of spar tube without play) was to have been accomplished by 1 March 1984, as required by DGAC AD 83-204-026(B) (which has been cancelled).

e.     For the horizontal stabilisers part number 315A35-10-000-2, the airworthiness aspects covered by DGAC AD 85-194-030(B) effective 27 November 1985, which is superseded and replaced by 96-277-037(A) R2 (this AD), remain applicable. These aspects are as follows:

Confirm that there are no traces of marking on the spar tube and rework the stabiliser support fittings in accordance with paragraph C.1. of SB No. 01.23.

3.    STABILISERS – ALL PART NUMBERS

Attach lockwire to the four attachment clamps of the half-shells in accordance with paragraph 2.B.2 of SB No. 55.01 Revision 4.

All stabilisers held as spares must be modified before installation on an aircraft, by the embodiment of modifications 07.2214 and 07.2215; and the inside of the tube visually inspected in accordance with paragraph 2.B.(1) of SB No. 55.01 Revision 4.

Note:  DGAC AD 96-277-037(A) R2 refers.

Compliance:

1.a. Inspect thereafter at intervals not to exceed 6 years.

1.b. As specified in Requirement 1.b.

1.c. (i)    After the last flight of the day.

1.c. (ii)   At intervals not to exceed 400 flight hours or 4 months, whichever occurs first.

1.d. Unless already accomplished, within 50 flight hours after 21 December 2006, and thereafter at intervals not to exceed 400 flight hours; or whenever the stabiliser is removed.

1.e. Unless already accomplished, before 21 January 2007.

2.a. Inspect thereafter at intervals not to exceed 6 years.

2.b. As specified in Requirement 2.b.

2.c. (i)  After the last flight of the day.

2.c. (ii) At intervals not to exceed 400 flight hours or 4 months, whichever occurs first.

2.d. As specified in Requirement 2.d.

2.e. Unless already accomplished, within 50 flight hours after 21 December 2006, and thereafter at intervals not to exceed 400 flight hours; or whenever the stabiliser is removed.

3.    Unless already accomplished, within 30 days after 21 December 2006.

This Airworthiness Directive becomes effective on 21 December 2006.

Background:

This Directive requires certain actions in order to improve the horizontal stabiliser fatigue strength.

David Villiers
Delegate of the Civil Aviation Safety Authority

7 November 2006