AD 65-28-02

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AD Number:
65-28-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Fairchild Model F-27 Series Airplanes
Subject:
Engine Mount Fittings
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/14/1965
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Superseded AD: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Superseded By: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: 65-28-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-169

AD NUMBER:   65-28-02

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

ACTION:  

SUMMARY:  

DATES:   Effective December 14, 1965.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
65-28-02 FAIRCHILD: Amdt. 39-169 Part 39 Federal Register December 14, 1965. Applies to Model F-27 Series Airplanes Incorporating Upper Engine Mount Fittings P/N's 27-503148-31, -32, -41, -42, -51, -52, -61, -62, and Lower Engine Mount Fittings P/N's 27-503149-11, -12, -31, -32, -41, and -42.

Compliance required as indicated.

To detect cracks in the engine mount attachment fittings, accomplish the following:

(a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the 250 hours' time in service before the effective date of this AD, inspect the engine mount fittings in accordance with (d).

(b) For engine mount fittings with 10,000 or more hours' time in service on the effective date of this AD, reinspect in accordance with (d) at intervals not to exceed 300 hours' time in service from the last inspection.

(c) For engine mount fittings with less than 10,000 hours' time in service on the effective date of this AD, reinspect in accordance with (d) before the accumulation of 10,150 hours' time in service, unless accomplished after the accumulation of 9,850 hours' time in service, and thereafter at intervals not to exceed 300 hours' time in service from the last inspection.

(d) Visually inspect for cracks each engine mount fitting (eight per airplane), on the forward side of the firewall, including all welds, using at least a 10-power glass or an FAA-approved equivalent. Clean all surfaces of each engine mount fitting prior to inspecting, (without removing fitting).

(e) If a crack is found during the inspection specified in (d) before further flight, replace the engine mount fitting with a part of the same part number that has been inspected in accordance with (d), or an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.

(f) 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.

This directive effective December 14, 1965.

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