AD 70-25-04

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AD Number:
70-25-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BEECH Model 65-90 Airplanes
Subject:
Cracking Of Wing Center Section
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/16/1971
Make:
Textron Aviation Inc.
Model:
65-90
Product Type:
Aircraft
Product Subtype:
Small 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Superseded AD: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Superseded By: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: 70-25-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1332

AD NUMBER:   70-25-04

SUBJECT HEADING:   Airworthiness Directives; BEECH Model 65-90 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 16, 1971.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
70-25-04 BEECH: Amdt. 39-1121 as amended by Amendment 39-1332. Applies to Model 65-90 (Serial Numbers LJ-1 through LJ-67) airplanes with 5,000 or more hours' time in service.

Compliance: Required as indicated.

To detect any cracking of certain wing center section and other wing panel front spar carry through structural components, within the next 100 hours' time in service after December 5, 1970, unless already accomplished, accomplish the following:

A) Visually inspect the lower wing skin area adjacent to each outer wing panel front spar attachment fitting for cracks in accordance with Beechcraft Service Instruction No. 0394- 018 or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, and thereafter repeat the inspection at intervals not to exceed 100 hours' time in service.

(1) If wing panel skin cracks are found at the most outboard screw hole as noted in Figure 1 of Beechcraft Service Instruction No. 0394-018, the wing structure must be inspected in accordance with Paragraphs B and D of this AD prior to returning the aircraft to service. In addition, if a skin crack is found at the most outboard screw hole, as indicated in said Figure 1, the Paragraph B inspections must be performed at intervals of not more than 300 hours, and the Paragraph D inspections must be performed at intervals of not more than 500 hours.

B) Inspect by visual and dye penetrant methods, the right and left lower forward outboard wing attachment fittings for cracks in accordance with Beechcraft Service Instruction No. 0394-018 or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, and thereafter repeat the inspection at intervals not to exceed 500 hours' time in service, except as noted in Paragraph A(1).

C) If fatigue cracks are found in either wing attach fitting during the inspections required by Paragraph B, prior to further flight -

(1) Both right and left outer wing panel lower forward spar caps including the wing attachment fittings and the skin panels adjacent to the outer panel wing attachment fittings must be replaced with new parts in accordance with the procedures, limitations and reinspection intervals specified in Beechcraft Service Instruction No. 0394-018, or later revision approved by the FAA.

(2) After one replacement of the assemblies listed in Paragraph C(1), replace the wing center section lower forward spar cap and fittings with new parts in accordance with Beechcraft Service Instruction No.0394-018, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.

D) Inspect the structural components set forth below and in Beechcraft Service Instruction No. 0394-018, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, by visual, eddy current and dye penetrant methods, as specified in the Service Instructions, and thereafter repeat the inspection at intervals not to exceed 1,000 hours' time in service, except as noted in Paragraphs (A)1 and D(8). The structural components to be inspected are as follows:

(1) Right and left lower forward wing attachment fitting of the center section main spar.

(2) Lower forward wing fitting-to-spar attachment area and the edges of the forward and aft flanges on the lower forward spar cap in the center section (outboard of each main gear wheel well).

(3) Lower forward spar cap in each main gear wheel well.

(4) Lower surface of the lower forward spar cap in the nacelle inboard of each main gear wheel well.

(5) Lower surface of the lower forward spar cap between each nacelle and the fuselage.

(6) The four universal rivet holes in the forward flange of the lower forward spar cap inboard of each nacelle in the area of the wing root rib.

(7) The lower forward spar cap within the fuselage.

(8) The centerline skin splice in the area between the forward and aft center section spars, and the fuselage formers along the centerline between the forward and aft center section spars. If fuselage former cracks are found in this area, they must be repaired in accordance with said Service Instruction prior to return to service and the 1,000 hour inspection interval must be reduced to not more than 500 hours.

E) If cracks are found during the inspections required by Paragraph D, except cracks located in the areas specified in Paragraph D(8), prior to further flight, replace the wing center section lower forward spar cap, both the right and left outer wing panel lower front spar caps including the wing attachment fittings and the skin panels adjacent to the outer panel wing attachment fittings with new production parts in accordance with Beechcraft Service Instruction No. 0394-018, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.

F) Aircraft logbook entries must be made and notification in writing must be sent to Chief, Engineering and Manufacturing Branch, FAA, Central Region, of the location and length of any cracks found during inspections required by this AD and also the total time in service of the component at the time the crack was discovered. Malfunction or Defect Report, FAA Form 8330-2, may be used for this purpose. (Report approved by the Bureau of the Budget under BOB No. 04-R0174.)

G) Replacement of parts required by Paragraphs C and E will permit the owner/operator to establish new initial inspection times in compliance with Paragraphs A and B.

H) Equivalent methods of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.

NOTE: The eddy current inspections required by this AD should be performed by certificated personnel trained and qualified in the operation of eddy current equipment. The replacement of critical parts such as the spar caps and wing attach fittings required by this AD should be performed by certificated personnel or facilities properly equipped to perform such repairs.

Amendment 39-1121 became effective December 5, 1970.

This amendment 39-1332 becomes effective November 16, 1971.

FOOTER: