AD 63-17-02

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AD Number:
63-17-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Fairchild Model F-27 Series Aircraft
Subject:
Nose Landing Gear Bolts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/13/1963
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Superseded AD: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Superseded By: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: 63-17-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   63-17-02

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

ACTION:  

SUMMARY:  

DATES:   Effective September 13, 1963.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
63-17-02 FAIRCHILD: Amdt. 602 Part 507 Federal Register August 14, 1963. Applies to Model F-27 Series Aircraft on which a Walter Kidde Spur Gear Nose Wheel Steering Actuator Assembly, P/N 891800 (STC SA1-574), has been installed.

Compliance required as indicated.

Due to failures of the mounting bolts, P/N's 244241 and 245804 in the nose gear pivot bracket, accomplish the following:

(a) On all affected aircraft that have not had the subject steering actuator assembly modified in accordance with Walter Kidde and Company, Inc., Service Bulletin No. 143 dated October 1962, or FAA approved equivalent, accomplish the following within the next 250 hours' time in service after the effective date of this AD and at intervals thereafter not to exceed 250 hours' time in service from the last inspection:

(1) Inspect the 4 mounting bolts, P/N's 244241 and/or 245804, for cracks using dye penetrant methods in conjunction with at least a 10-power magnifying lens, or FAA approved equivalent inspection. Give particular attention to the necked-down area of the bolt where the shank meets the threads. Inspection may be accomplished without jacking-up the aircraft only if one bolt at a time is removed, inspected, and then replaced and properly torqued, before inspection of the second bolt is attempted.

(b) If a crack is found, accomplish one of the following before further flight except that a ferry flight may be made in accordance with the provisions of CAR 1.76.

(1) Replace any cracked bolt with a new one of the same type or an FAA approved equivalent and continue inspecting in accordance with (a) or

(2) Modify the subject steering actuator assembly in accordance with Walter Kidde and Company, Inc., Service Bulletin No. 143 dated October 1962, or an FAA approved equivalent.

(c) The repetitive inspections of the steering actuator assembly, as prescribed in (a) may be discontinued on aircraft modified in accordance with (b)(2) or an FAA approved equivalent.

(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 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 such operator.

(Walter Kidde and Company, Inc. Service Bulletin No. 143 dated October, 1962, covers this subject.)

This directive effective September 13, 1963.

FOOTER: