AD 69-05-02

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AD Number:
69-05-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Fairchild Model FH-227 Airplanes
Subject:
Wing Panel
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/18/1976
Make:
Maryland Air Industries, Inc.
Model:
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Superseded AD: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Superseded By: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: 69-05-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2641

AD NUMBER:   69-05-02

SUBJECT HEADING:   Airworthiness Directives; Fairchild Model FH-227 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective June 18, 1976.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
69-05-02 FAIRCHILD: Amendment 39-729 as amended by Amendment 39-1588 is further amended by Amendment 39-2641. Applies to FH-227 Type Airplanes Certificated in all categories.

Compliance required as indicated.

To detect the development of cracks in the wing area, accomplish the following:

(a) Within 25 hours time in service after the accumulation of the specified hours in service, unless already accomplished, inspect or continue to inspect in accordance with Fairchild Service Bulletin 51-1, as amended by Revision 6, of December 12, 1975 or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region or with an approved equivalent inspection.

(b) Where a visual inspection may be accomplished in lieu of x-ray, at least a 10-power glass must be used.

(c) For those aircraft incorporating Fairchild Service Bulletin 51-1, Appendix No. 1, dated January 5, 1973, or an approved equivalent special structural inspection and alteration, the inspection interval for the outer wing panel without cracks remains at 1200 hours. If any cracks were discovered prior to the alteration the inspection interval will be that specified in paragraph 1.D(1) of the Appendix.

(d) If new cracks are found or if repaired cracks are found to be propagating, replace the cracked part with a part of the same part number or with an approved equivalent part, or incorporate an approved repair before further flight. However, upon request, with descriptive information of the crack and proposed operating limitations submitted through an FAA maintenance inspector, the flight of the airplane in accordance with FAR 21.197 to a base where the repair can be made, may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

(e) Equivalent inspection, repairs or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

(f) Upon request, with substantiating data submitted through an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

Amendment 39-729 was effective March 12, 1969.
Amendment 39-1588 was effective January 31, 1973.
This amendment 39-2641 is effective June 18, 1976.

NOTE: Amendment 39-2641 was distributed on June 7, 1976, as AD 76-12-04. The issuing office intended Amendment 39-2641 to be published as a revision to AD 69-5-2. Accordingly, the AD is being republished to reflect the correct AD number and AD 76-12-04 is cancelled.

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