AD 83-03-03

AD Final Rules - DRS_83-03-03.html
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AD Number:
83-03-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; GARLICK HELICOPTERS, HAWKINS & POWERS AVIATION, INC., WILCO AVIATION (BELL...Show more
Subject:
Tail Boom and Fin
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/14/1983
Make:
California Department of Forestry | Richards Heavylift Helo, Inc. | Rotorcraft Development Corporati...Show more
Model:
UH-1F | UH-1A | UH-1B | UH-1E | UH-1L
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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 83-03-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4556

AD NUMBER:   83-03-03

SUBJECT HEADING:   Airworthiness Directives; GARLICK HELICOPTERS, HAWKINS & POWERS AVIATION, INC., WILCO AVIATION (BELL) Model UH-1 Series Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective March 14, 1983.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
83-03-03 GARLICK HELICOPTERS, HAWKINS & POWERS AVIATION, INC., WILCO AVIATION (BELL): Amendment 39-4556. Applies to Model UH-1 series helicopters certificated in restricted category.

Compliance is required as indicated, unless already accomplished.

To detect cracks and to prevent possible failure of the tail boom and fin, accomplish the following:

Within the next 30 hours' time in service after the effective date of this AD:

a. Conduct the following inspections:

(1) Visually inspect the tail boom skin joint at tail boom Station 194 for fretting or cracking (inspect 10 inches forward and 10 inches aft of Station 194).

(2) Visually inspect the vertical fin front spar cap at its intersection with the tail rotor gear box support fitting for cracks.

(3) The areas to be inspected are shown in Figure 1.

b. For aircraft found to have fretting or cracks by the inspections of paragraph a. above and for aircraft with more than 1,000 hours' time in service, conduct a radiographic inspection of the tail boom Station 194 splice joint in accordance with Advisory Circulars 43-3 (Chapter 2) and 43-13-1A (paragraph 298) to MIL-STD-453 requirements, or FAA approved equivalent.

c. After the initial inspections -

(1) Visually inspect the tail boom skin and fin spar cap area in accordance with paragraph a. above, at intervals not to exceed 100 hours' time in service from the last radiographic inspection.

(2) Radiographically inspect the tail boom skin in accordance with paragraph b. above at intervals not to exceed 500 hours' time in service from the last radiographic inspection.

d. Replace cracked skin panels with serviceable panels.

e. Replace cracked fin spar caps with serviceable parts.

f. Any equivalent method of compliance with this AD must be approved by the Manager, Aircraft Certification Division, Southwest Region, Federal Aviation Administration.

g. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Manager, Aircraft Certification Division, FAA Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.

h. In accordance with FAR 21.197, flight is permitted to a base where the inspections required by this AD may be accomplished.

This amendment becomes effective March 14, 1983.




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