AD 77-07-08

AD Final Rules - DRS_77-07-08.html
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AD Number:
77-07-08
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Fairchild (Hiller) Models 1100 and FH 1100 Helicopters
Subject:
Tail Rotor Tension Torsion Bars
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/05/1977
Make:
FH1100 Manufacturing Corporation
Model:
1100 | FH-1100
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Superseded AD: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Superseded By: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: 77-07-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2992

AD NUMBER:   77-07-08

SUBJECT HEADING:   Airworthiness Directives; Fairchild (Hiller) Models 1100 and FH 1100 Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective August 5, 1977.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
77-07-08 FAIRCHILD (HILLER): Amendment 39-2866 as amended by Amendment 39-2992. Applies to Model 1100 and FH-1100 type helicopters certified in all categories.

Compliance required as follows:

To detect improper surface finish in the bolt holes at each end of the tail rotor tension torsion bars, P/N's 24-55106 which could lead to cracking of the bar plates, accomplish the following within the next 25 hours in service after the effective date of this AD unless already accomplished.

Inspect the two tail rotor tension torsion bars, P/N's 24-55106 which have serial numbers prior to 1922 or illegible serial numbers, in accordance with Fairchild FH-1100 Service Bulletin No. SBFH1100-55-2A dated 19 January 1977, Section 2 "Accomplishment Instructions" or equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

If tension torsion bars are found unacceptable in accordance with the service bulletin or those procedures approved by the Chief, Engineering and Manufacturing Branch, replace the bar with one that has been inspected and found acceptable in accordance with the service bulletin or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection interval specified in this AD.

Amendment 39-2866 became effective April 11, 1977.
This Amendment 39-2992 becomes effective August 5, 1977.

FOOTER: