AD 68-26-03

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AD Number:
68-26-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CANADAIR Model CL-44D4 Airplanes
Subject:
Stabilizer Rib Cracks
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/19/1968
Make:
Bombardier Inc.
Model:
CL-44D4
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Superseded AD: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Superseded By: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: 68-26-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-693

AD NUMBER:   68-26-03

SUBJECT HEADING:   Airworthiness Directives; CANADAIR Model CL-44D4 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 19, 1968.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
68-26-03 CANADAIR: Amendment 39-693. Applies to CL-44D4 Type airplanes.

To detect cracks in stabilizer interspar ribs at Stations 123, 141 and 159, accomplish the following:

(a) Within the next 100 hours time in service after the effective date of this A.D. unless accomplished within the last 400 hours time in service, and at intervals thereafter not to exceed 500 hours time in service from the last inspection, inspect the rib caps of P/N 44-A67035- A-B, P/N 44-A67038-A-B, and P/N 44-A24301-A-B for cracks using a 5-power or greater boroscope or an FAA-approved equivalent inspection.

(b) Replace cracked parts before further flight with a part of the same part number or an FAA-approved equivalent part, or repair cracked parts in accordance with the Canadair CL-44 Structural Repair Manual or an FAA-approved equivalent repair.

(c) The repetitive inspection required by (a) need not be performed, if the stabilizer has been altered in accordance with Canadair Service Bulletin No. 286, or an FAA-approved equivalent alteration.

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

(e) The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA maintenance inspector.

This amendment is effective December 19, 1968.

FOOTER: