AD 85-21-04

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AD Number:
85-21-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Fairchild Models F27 and FH227 Series Airplanes
Subject:
Rod Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/14/1985
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Superseded AD: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Superseded By: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: 85-21-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5150

AD NUMBER:   85-21-04

SUBJECT HEADING:   Airworthiness Directives; Fairchild Models F27 and FH227 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 14, 1985.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
85-21-04 FAIRCHILD: Amendment 39-5150. Applies to Models F27 and FH227 series airplanes, certificated in any category. Compliance required as indicated. To detect cracks due to stress corrosion in the riveted rod end assembly, part number (P/N) 27-727404-11, on rudder control push-pull tubes, P/N's 27-727402-11 (or -41) and -31 (or -51), 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 150 hours time in service, and thereafter at intervals not to exceed 200 hours in service from the last inspection, inspect the riveted rod end, P/N 27-727404-3, of the rudder control push-pull tubes, P/N's 27-727402-11 (or -41) and -31 (or -51), for cracks, in accordance with Fairchild Service Bulletin FH227-27-31 for Model FH227 airplanes (serial numbers 501 through 578) and Service Bulletin F27-27-76 for Model F27 airplanes (serial numbers 1 through 128).

B. If cracks are found, the rod assembly must be replaced before further flight with a rod of the same part number, or FAA-approved equivalent part, that has been inspected and found serviceable in accordance with paragraph A., above; or replaced before further flight with a new rod end assembly, P/N 27-727404-31, or FAA-approved equivalent part.

C. Installation of the new assembly, P/N 27-727404-31, may be considered terminating action for the repetitive inspections specified in paragraph A., above.

D. Aircraft maintenance record entries must be made and a report in writing of the initial inspection findings, positive or negative, must be submitted to the FAA, New York Aircraft Certification Office, Room 202, Attention: ANE-170, 181 S. Franklin Avenue, Valley Stream, New York 11581. The report must state the location and length of any crack found during the initial inspection, and include the total time in service of the component at the time the crack was discovered. (Reporting requirement approved by the Office of Management and Budget under OMB No. 2120-0056.)

E. Upon the request of an operator, an FAA Maintenance Inspector, subject to prior approval by the Manager, New York Aircraft Certification Office, FAA, New England Region, may adjust the inspection times specified in this AD to permit compliance at an established inspection period of that operator if the request contains substantiating data to justify the change for that operator.

F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the inspection requirements of this AD.

G. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region.

All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Fairchild Industries, Inc., Fairchild Republic Division, Hagerstown, Maryland 21740. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the FAA, New England Region, New York Aircraft Certification Office, 181 S. Franklin Avenue, Room 202, Valley Stream, New York 11581.

This amendment becomes effective November 14, 1985.

FOOTER: