AD 80-22-09

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AD Number:
80-22-09
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA Model A109A Series Helicopters
Subject:
Engine Mount Structure
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/06/1980
Make:
Agusta S.p.A.
Model:
A109A | A109A 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Superseded AD: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Superseded By: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: 80-22-09
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3957

AD NUMBER:   80-22-09

SUBJECT HEADING:   Airworthiness Directives; COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA Model A109A Series Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective November 6, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-22-09 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA: Amendment 39- 3957. Applies to Model A109A series helicopters, certificated in all categories, except for the following serial numbered helicopters:

7107	7119	7142	7150
7109	7128	7143	7152
7110	7132	7144	7158
7113	7138	7145	7160
7114	7140	7148	7166 and subsequent.
7117			
Compliance required as indicated, unless already accomplished.

To prevent failure of the engine mount structure, accomplish the following:

(a) Within the next 25 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 25 hours time in service since the last inspection, visually inspect the forward mounting tab of the aluminum engine outer lateral fitting, P/N 109-0320-97- 4, for cracks in accordance with "ACCOMPLISHMENT INSTRUCTIONS" of Costruzioni Aeronautiche Giovanni Agusta Service Bulletin No. 109-18, dated April 27, 1979 (hereinafter referren to as the Service Bulletin), or an FAA-approved equivalent.

(b) If, as a result of the inspections required in paragraph (a) of this AD, no cracking is found, return the helicopter to service and continue to inspect in accordance with paragraph (a) or comply with paragraph (d) of this AD.

(c) If, as a result of any inspection required in paragraph (a) of this AD, cracking is found, before further flight, except as provided in paragraph (e) of this AD, - -

(1) Replace the cracked fitting with a serviceable fitting of the same part number and continue to inspect in accordance with paragraph (a) of this AD; or

(2) Replace the cracked fitting with a new steel fitting, P/N 109-0320-97-6, or an FAA-approved equivalent.

(d) Compliance with the repetitive inspections required by paragraphs (a), (b) and (c)(1) of this AD may be discontinued when a steel fitting, P/N 109-0320-97-6, or an FAA approved equivalent, is installed.

(e) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the maintenance required by this AD may be accomplished. Ferrying of the helicopter with a failed fitting or an engine inoperative is not permitted.

(f) If an equivalent means of compliance is used in complying with paragraphs (a), (c)(2) and (d) of this AD, that equivalent means must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belguim.

(g) Upon request of an operator, the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Office, may approve an equivalent modification or replacement fitting provided the request is made through an FAA Maintenance Inspector and the request contains substantiating data to justify the request for that operator.

This amendment becomes effective November 6, 1980.

FOOTER: