AD 82-18-04

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AD Number:
82-18-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE Model SA 330F, SA 330G, and SA...Show more
Subject:
Main Bevel Gear Wheel
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/07/1982
Make:
Airbus Helicopters
Model:
SA330F | SA330G | SA330J
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Superseded AD: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Superseded By: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: 82-18-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4441

AD NUMBER:   82-18-04

SUBJECT HEADING:   Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE Model SA 330F, SA 330G, and SA330J Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective September 7, 1982.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
82-18-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4441. Applies to Model SA 330F, SA 330G, and AS 330J helicopters certificated in all categories and equipped with any dash number of main gearbox (MGB), Part Number (P/N) 330A32.2000, 330A32.3000, 330A32.4000, or 330A32.6000, which has not incorporated Aerospatiale modification No. AMS 330A07.52.171, or for which the Spectrometric Oil Analysis Procedure (SOAP) is not included in the routine maintenance of the MGB.

Compliance is required as indicated unless already accomplished.

To prevent possible bearing failure within the MGB due to fretting in the main bevel gear wheel-to-shaft junction, accomplish the following:

(a) In accordance with the instructions in paragraphs 1.C(1) and 1.C(2) of Aerospatiale SA 330 PUMA Service Bulletin No. 05.64, dated April 28, 1982, or an FAA approved equivalent, gain access and inspect the bolted junction of the main bevel gear wheel and its shaft inside the MGB for evidence of fretting. Compliance with this inspection is required within the following time periods:

(1) For an overhauled MGB:

(i) Within the next 50 hours' time in service after the effective date of this AD, if the MGB has accumulated 200 hours' or more since overhaul on the effective date of this AD, or

(ii) Before reaching 250 hours' time in service since the last overhaul, if the MGB has accumulated less than 200 hours' time in service since the overhaul on the effective date of this AD.

(2) For an MGB which has not been overhauled:

(i) Within the next 100 hours' time in service after the effective date of this AD, if the MGB has accumulated 1,100 hours' or more time in service on the effective date of this AD, or

(ii) Before reaching 1,200 hours' time in service, if the MGB has accumulated less than 1,100 hours' time in service on the effective date of this AD.

(b) When no evidence of fretting is found during the inspection required by paragraph (a) of this AD, the MGB may be returned to service in accordance with paragraph 1.C(4) of Aerospatiale SA 330 PUMA Service Bulletin No. 05.64 or FAA approved equivalent.

(c) When evidence of fretting is found during the inspection required by paragraph (a) of this AD, before further flight and in accordance with the instructions given in paragraph 1.C(3)(b) of Aerospatiale SA 330 PUMA Service Bulletin No. 05.64 or an FAA approved equivalent, inspect each of the 18 nuts on the bolts joining the main bevel gear wheel to its shaft for rotation/slippage. Dispose of findings as follows:

(1) When nut rotation/slippage is found, remove the MGB from service before further flight.

(2) When no nut rotation/slippage is found, the MGB may be returned to service with repetitive nut inspections not to exceed 400 hours' time in service since the last inspection.

(d) A special flight permit may be issued, in accordance with FAR 21.197 and 21.199, to operate the helicopter to a base where the requirements of paragraph (c) of this AD may be accomplished.

(e) Equivalent means of compliance must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium.

This amendment becomes effective September 7, 1982.

FOOTER: