AD 84-13-06 R2

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AD Number:
84-13-06 R2
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA S.p.A. Model A109A and A109A II ...Show more
Subject:
Tail Rotor Blade Grip
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/30/1987
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Superseded AD: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Superseded By: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: 84-13-06 R2
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5682

AD NUMBER:   84-13-06 R2

SUBJECT HEADING:   Airworthiness Directives; COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA S.p.A. Model A109A and A109A II Series Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective August 30, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
84-13-06 R2 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA S.p.A.: Priority letter AD 84-13-06 as amended by Amendment 39-5043 is further amended by Amendment 39- 5682. Applies to Model A109A and A109A II series helicopters certificated in any category and equipped with P/N 109-0132-02-11 or -15 tail rotor blades.

Compliance is required as indicated unless already accomplished.

To prevent possible hazards in flight associated with cracking of the tail rotor blade grip, accomplish the following:

(a) Within the next 10 hours time in service, inspect the tail rotor blade grip in accordance with Part I of Agusta Service Bulletin (SB) 109-51, Revision A, or an FAA-approved equivalent, and at each additional 25 hours time in service, accomplish the inspection of Part III of Agusta SB 109-51, Revision A, or an FAA-approved equivalent.

(b) Prior to the first flight of each day, comply with Part II of the accomplishment instructions of Agusta SB 109-51, Revision A, or an FAA-approved equivalent. This accomplishment may be conducted by the pilot.

(c) Remove from service any tail rotor blade where cracking is found and replace with a serviceable part prior to next flight.

(d) An equivalent method of compliance with this AD may be used when approved by the Manager, Brussels Aircraft Certification Office.

Priority letter AD 84-13-06 was effective June 29, 1984.

Amendment 39-5043 was effective May 13, 1985.

This amendment, 39-5682, becomes effective August 30, 1987.

FOOTER: