AD 58-14-01

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AD Number:
58-14-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Sud Aviation Model Alouette II SE 3130 Helicopters
Subject:
Rotor Blade Bonding
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
Make:
Airbus Helicopters
Model:
SE 3130-Alouette II
Product Type:
Aircraft
Product Subtype:
Rotorcraft
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 58-14-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   58-14-01

SUBJECT HEADING:   Airworthiness Directives; Sud Aviation Model Alouette II SE 3130 Helicopters

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
58-14-01 SUD AVIATION: Applies to All Alouette II SE 3130 Helicopters Equipped With Tail Rotor Blade Model Numbers 34.20.000, 34.20.000.50, 34.20.000.51, and 34.30.000.

Compliance required prior to next flight and each 5 hours of operation thereafter.

Two cases of defective bonding at the outboard end of the root end side plates of the tail rotor blades have been found. In order to preclude any possible fatigue failures of the blade, Sud Aviation has issued the following corrective measures which the French SGACC considers mandatory:

Inspection
A. Blades with rigid flapping restrainer. (Aircraft Numbers 1137 and above or aircraft incorporating modification V.14.)

1. Saturate with turbine oil (Spec. AIR 3512 or DED 2479/6, Shell turbine oil No. 9 or Esso aviation oil No. 57) the edge of the side plate and the bead of adhesive at the outboard end of the side plate.

2. Move blade to and from by pushing and pulling blade tip alternately four or five times respectively, applying a load of approximately 13 lb. (check with spring balance).

3. In the case of a defective blade, the oil will flow in and out and, at the same time, air bubbles may be produced.

4. If in doubt, wipe the side plate and repeat the above loading procedure.

B. Blades with earlier type flapping restrainer. (Aircraft Numbers 1136 and below which do not incorporate modification V.14.)

The previously described inspection procedure cannot be applied without risking distortion of the flapping restrainers.

The procedure may, however, be applied if the blades are removed and are clamped in a vise over the two inboard blade-cuff retaining bolts (bolts nearest root end of blade).

To avoid blade removal and inspection in a vise, the tools may be fabricated in order to rigidly support the blade root on the helicopter.

The tools can simply consist of a wood block cut to proper length so as to rest at one end against the two tail gearbox nuts and at the other end against the blade-cuff bolts.

To hold the blade in the other direction, strap the blade and the tail gearbox housing as shown in the sketch in the referenced Service Bulletin, using a cable cut to the proper length or, alternatively, a non-elastic strap.

The inspection procedure is the same as previously described.

C. Defective blades shall be retired from service immediately. Others may be left in service as long as the bonding is satisfactory up to a maximum of 300 hours.

The FAA concurs with this action and considers compliance there with mandatory.

(Sud Aviation Helicopter Service Bulletin No. AL 34.11.131/A covers the same subject.)

This supersedes AD 58-13-04.

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