AD 82-04-04

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AD Number:
82-04-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; COSTRUZIONI AERONAUTICHE GIOVANNI (AGUSTA): Model A109A Series Helicopters
Subject:
Tail Boom Assemblies
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/19/1982
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Superseded AD: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Superseded By: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: 82-04-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4314

AD NUMBER:   82-04-04

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

ACTION:  

SUMMARY:  

DATES:   Effective February 19, 1982.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
82-04-04 COSTRUZIONI AERONAUTICHE GIOVANNI (AGUSTA): Amendment 39- 4314. Applies to all Model A109A series helicopters equipped with tail boom assembly up to and including Serial Numbers 056 and Serial Numbers 030EM through 107EM, inclusive, certificated in all categories.

Compliance is required as indicated.

To detect possible cracks and prevent structural failure of the tail boom assembly and possible loss of control of the helicopter, accomplish the following:

(a) For tail boom assemblies serial numbers up to and including 056 and 030EM through 057EM, accomplish the following:

(1) Before the first flight of each day, unless the tail boom has been modified in accordance with Agusta Kit No. 109-0820-1 or -3, visually check the tail fin outer skin areas shown in Figure 1 and 2 of Agusta Technical Bulletin No. 109-23, Revision A dated June 17, 1981, (hereinafter referred to as Technical Bulletin 23A) for cracks, missing or loose rivets, and breaking of adhesive.

(2) Within 25 hours' time in service after the effective date of this AD, and thereafter at intervals not exceeding 25 hours' time in service from the last inspection unless the tail boom has been modified in accordance with Agusta Kit No. 109-0820-23-3, inspect the tail boom in accordance with "Accomplishment Instructions," Part II, of the Technical Bulletin 23A. NOTE: Tail booms incorporating modification Kit No. 109-0820-23-1 are still subject to this inspection.

(3) When cracks, missing or loose rivets, or breaking of adhesive are found during the checks or inspections required in subparagraphs (a)(1) or (a)(2), repair the tail boom assembly as necessary, in accordance with "Accomplishment Instructions," Part III, of the Technical Bulletin 23A before further flight, except the aircraft may be flown in accordance with FAR 21.197 and 21.199 to a base where the repair may be performed.

(b) For tail boom assemblies serial numbers 058EM through 107EM, accomplish the following:

(1) Within 25 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 25 hours' time in service from the last inspection, unless the tail boom has been modified in accordance with Agusta Kit No. 109-0950-54, inspect the tail boom elevator support frames in accordance with Part I, of Technical Bulletin No. 109-31 (hereinafter referred to as Technical Bulletin 31) for cracks in the support frames.

(2) When cracks in the frames are found, repair the tail boom assembly, as necessary, before further flight in accordance with Part II of Technical Bulletin 31, except the aircraft may be flown in accordance with FAR 21.198 and 21.199 to a base where the repair may be performed.

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

(d) Installation of Repair Modification Kit No. 109-0950-54, "Elevator Support Frames Structural Repair" contained in Technical Bulletin 31 is equivalent to the elevator support frame repair (Modification No. 109-0820-23-3) that is contained in Technical Bulletin 23A.

(e) The checks specified in subparagraph (a)(1) may be performed by the pilot. NOTE: For the requirements regarding the listing of compliance and method of compliance with this AD in the aircraft's permanent maintenance record, see FAR 91.173.

This amendment becomes effective February 19, 1982.

FOOTER: