AD 67-12-04

AD Final Rules - DRS_67-12-04.html
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AD Number:
67-12-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Fairchild-Hiller Models F-27 Series and FH-227 Series Airplanes
Subject:
Rudder Horn Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/08/1967
Make:
Maryland Air Industries, Inc.
Model:
F-27 | F-27A | F-27B | F-27F | F-27G | F-27J | F-27M | FH-227 | FH-227B | FH-227C | FH-227D | FH-227E
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 67-12-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-391

AD NUMBER:   67-12-04

SUBJECT HEADING:   Airworthiness Directives; Fairchild-Hiller Models F-27 Series and FH-227 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 8, 1967.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-12-04 FAIRCHILD-HILLER: Amdt. 39-391 Part 39 Federal Register April 8, 1967. Applies to Models F-27 Series and FH-227 Series Airplanes.

Compliance required as indicated.

To detect cracks in the rudder horn assembly, accomplish the following:

(a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 450 hours' time in service, and thereafter at intervals not to exceed 500 hours' time in service from the last inspection, comply with (b).

(b) Visually inspect the rudder horn assembly, P/N 27-243018-11, for cracks, using a glass of at least 10-power, or use an equivalent inspection approved by an FAA maintenance inspector. If a crack is found comply with (c) before further flight.

(c) Replace a cracked part with a part of the same part number that has been inspected in accordance with (b), or use an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.

(d) The repetitive inspection required by (a) may be discontinued when a modification, approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region is incorporated.

(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the initial compliance time and the repetitive inspection interval specified in this AD if the request contains substantiating data to justify the increase for that operator.

This directive effective April 8, 1967.

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