AD 67-11-02

AD Final Rules - DRS_67-11-02.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
67-11-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Fairchild-Hiller Model F-27 Series Airplanes
Subject:
Cracks in Lower Fuselage Exterior
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/05/1967
Make:
Maryland Air Industries, Inc.
Model:
F-27 | F-27A | F-27B | F-27F | F-27G | F-27J | F-27M
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Superseded AD: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Superseded By: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: 67-11-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-385

AD NUMBER:   67-11-02

SUBJECT HEADING:   Airworthiness Directives; Fairchild-Hiller Model F-27 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 5, 1967.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-11-02 FAIRCHILD-HILLER: Amdt. 39-385 Part 39 Federal Register April 5, 1967. Applies to Model F-27 Series Airplanes, Serial Numbers 1 through 19 Except Serial Numbers 7, 10, 13 and 17.

Compliance required as indicated.

To detect cracks in the lower fuselage exterior skins, 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 350 hours' time in service, and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, visually inspect the fuselage skins between stringers 7 and 8 left and stringers 44 and 45 right from Fuselage Station 198 to Station 510, or use an equivalent inspection approved by an FAA maintenance inspector. If cracks are found, comply with (b) before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed.

(b) Repair cracked parts in accordance with Fairchild-Hiller Service Bulletin No. 53-48 dated February 7, 1967, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or equivalent approved by an FAA maintenance inspector, or replace them with an unused part of the same part number or an equivalent part approved by an FAA maintenance inspector.

(c) The repetitive inspection required by (a) may be discontinued on those skin panels replaced in accordance with Fairchild-Hiller Service Bulletin No. 53-48, dated February 17, 1967, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or an equivalent modification approved by an FAA maintenance inspector.

(d) 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 5, 1967.

FOOTER: