AD 81-06-04

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AD Number:
81-06-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE Model SE313, SA315, SA316, SA3...Show more
Subject:
Transmission Deck & Bellcrank Support
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/20/1981
Make:
Airbus Helicopters
Model:
SA 318B-Alouette Astazou | SA 318C-Alouette Astazou | SA.315B Alouette III | SA.316B Alouette III | ...Show more
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Superseded AD: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Superseded By: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: 81-06-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4064

AD NUMBER:   81-06-04

SUBJECT HEADING:   Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE Model SE313, SA315, SA316, SA318, and SA319 Series Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective March 20, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
81-06-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39-4064. Applies to Model SE313, SA315, SA316, SA318, and SA319 series helicopters, certificated in all categories, that do not have Aerospatiale Modification No. AM 2195 incorporated.

Compliance required as indicated.

To detect and prevent possible fatigue cracks and failures of the forward transmission deck support and the flight control bellcrank support accomplish the following, unless already accomplished:

(a) For helicopters which on the effective date of this AD, have 375 or more hours' time in service since new or since last overhaul, inspect in accordance with paragraph (c) of this AD, within the next 25 hours' time in service.

(b) For those helicopters which on the effective date of this AD, have less than 375 hours' time in service since new or overhaul, inspect in accordance with paragraph (c) of this AD before the accumulation of 400 hours' time in service.

(c) Visually inspect for cracks and deformation on the lower side of transmission deck stringer, and using the dye penetrant method, inspect for cracks in the inner bending radius of the stringer in accordance with the applicable Aerospatiale Service Bulletin Number 05.17 or Number 05.69 each dated December 15, 1980, or an FAA approved equivalent.

(d) If no cracks are found as the result of the inspection required in paragraphs (a), (b), (d), or (e) of this AD:

(1) Before further flight install two additional clamps P/N 55212.280BGZ, unless already accomplished, in accordance with Aerospatiale SA315 Service Bulletin Number 53.02 revised June 12, 1978, for Model SA315 and Service Bulletin 53.32, revised June 12, 1978, for all other models, or FAA approved equivalent, and return the aircraft to service.

(2) Repeat the inspections required by paragraph (c) of this AD at intervals not to exceed 400 hours' time in service since the last inspection, or comply with paragraph (f) of this AD.

(e) If deformation or cracks are found as a result of the inspection required in paragraphs (a), (b), (d), or (e) of this AD, before further flight:

(1) Replace the Z stringer with a serviceable stringer of the same part number and install clamps specified in subparagraph (d)(1) of this AD unless already installed, or

(2) Replace the transmission deck, install clamps specified in subparagraph (d)(1) of this AD unless already installed, and repeat the inspections required by paragraph (c) of this AD at intervals not to exceed 400 hours' time in service since the last inspection, or

(3) Comply with paragraph (f) of this AD.

(f) The repetitive inspections required in paragraphs (d) and (e) of this AD may be discontinued when the helicopter is modified in accordance with AM 2195 or Supplemental Type Certificate (STC) No. SH4266SW.

NOTE: MODIFICATION AM 2195 is the subject of Aerospatiale Service Bulletin Numbers 53.05 for the Model SA315, Number 53.35 for the models SE313 and SA318, Number 53.36 for the models SA316 and SA319, all dated December 30, 1980. STC SH4266SW provides for use of alternate parts.

(g) In accordance with FAR 21.197, flight is permitted to a base where the inspection and repairs required by this AD may be accomplished, provided satisfactory operation of the flight control system has been established prior to the flight.

(h) The Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Region, c/o American Embassy, Brussels, Belgium, may approve equivalent methods of repair or modifications when the request is submitted through an FAA maintenance inspector and contains adequate supporting data.

This amendment becomes effective March 20, 1981.

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