AD 65-05-04

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AD Number:
65-05-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Fairchild Model F-27 Series Aircraft
Subject:
Rudder Trim Tab
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/25/1965
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Superseded AD: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Superseded By: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: 65-05-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-40

AD NUMBER:   65-05-04

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

ACTION:  

SUMMARY:  

DATES:   Effective February 25, 1965.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
65-05-04 FAIRCHILD: Amdt. 39-40 Part 39 Federal Register February 25, 1965. Applies to Model F-27 Series Aircraft Serial Numbers 1 through 107.

Compliance required as indicated.

To prevent damage to the rudder and rudder trim tab from rudder vibration, accomplish the following:

(a) Within 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 75 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, inspect the rudder trim tab for cracks in accordance with Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.

(b) If a crack is found, modify the rudder trim tab in accordance with Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, before further flight, except that one flight may be made in accordance with the provisions of FAR 21.197 to a base where the repair can be made. During this flight, a maximum operating limit speed (Vmo) of 160 knots CAS or MACH number 0.35 shall be observed.

(c) Inspect in accordance with Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965, aircraft modified in accordance with (b) prior to the accumulation of 600 hours' time in service after modification, and thereafter at intervals not to exceed 150 hours' time in service from the last inspection.

(d) Within the next 100 hours' time in service after the effective date of this amendment unless already accomplished, modify the rudder trim tab in accordance with Fairchild Alert Bulletin No. 27-39A, dated March 12, 1965, or later FAA-approved revision, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.

(e) The repetitive inspections required by (a) and (c) may be discontinued when the modification required by (d) is incorporated.

(f) Upon request of the operator, an FAA maintenance inspectors, 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.

(Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965, covers this subject.)

This directive effective February 25, 1965.
Revised May 13, 1965.

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