AD 71-20-06

AD Final Rules - DRS_71-20-06.html
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AD Number:
71-20-06
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CANADAIR Model CL-44D4 and CL-44J Aircraft
Subject:
Horizontal Stabilizer
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/21/1980
Make:
Bombardier Inc.
Model:
CL-44D4 | CL-44J
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Superseded AD: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Superseded By: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: 71-20-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3699

AD NUMBER:   71-20-06

SUBJECT HEADING:   Airworthiness Directives; CANADAIR Model CL-44D4 and CL-44J Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective February 21, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
71-20-06 CANADAIR: Amendment 39-1300 as amended by Amendment 39-3699. Applies to all Canadair Model CL-44D4 and CL-44J aircraft.

Compliance required as indicated.

Within the next 300 hours time in service after the effective date of this AD, unless already accomplished within the last 4500 hours time in service and at intervals not exceeding 4800 hours time in service, accomplish the following:

(a) Inspect horizontal stabilizer front spar web, spar cap, and local structure at all stations from station 22 left to station 22 right for cracks in accordance with the inspection procedure defined in paragraphs 3, 3.1, and 3.2 of Canadair Service Information Circular No. 377-CL-44 dated May 20, 1971, as amended by amendment A, dated May 15, 1979, or in accordance with an FAA approved, equivalent inspection.

(b) If cracks are found in the spar web, spar caps, or local structure, repair or replace damaged parts before further flight with unused parts or with equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed.

(c) Repair procedures required by paragraph (b) must be in accordance with Canadair CL-44D4 Structural Repair Manual or an equivalent repair procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

(d) The repetitive inspection time may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region upon receipt of substantiating data submitted through an FAA Maintenance Inspector.

Amendment 39-1300 was effective October 5, 1971.

This Amendment 39-3699 is effective February 21, 1980.

FOOTER: