AD 83-10-05

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AD Number:
83-10-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CANADAIR Model CL-44D4 and CL-44J Airplanes
Subject:
Horizontal Stabilizer Rear Attachment Fittings
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/06/1983
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Superseded AD: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Superseded By: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: 83-10-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4654

AD NUMBER:   83-10-05

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

ACTION:  

SUMMARY:  

DATES:   Effective June 6, 1983.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   83-10-05 CANADAIR: Amendment 39-4654. Applies to all Canadair Model CL-44D4 and CL-44J airplanes. Compliance required as indicated unless previously accomplished. To detect cracks in the horizontal stabilizer rear attachment fittings, accomplish the following:

1. Within the next 200 hours time in service and thereafter at intervals not to exceed 2000 hours time in service, inspect the horizontal stabilizer rear spar attachment fittings, Part Numbers 44-A45022A and 44-A45022B, for cracks in accordance with Paragraph 3.5 and 3.6 of Canadair Service Information Circular No. 379-CL44, Issue 3, dated February 23, 1982. Ensure that the lugs are properly shimmed in accordance with paragraph 4.1 of the circular. If a crack is found the length of which is less than half the width of the lug, repeat the inspection every 100 hours time in service and replace the fitting within the next 500 hours time in service. When a crack is found the length of which extends to or beyond half the width of the lug, replace the fitting prior to further flight in accordance with the circular.

2. Within the next 200 hours time in service and thereafter at intervals not to exceed 2000 hours time in service, inspect the reinforcing channels, Part Numbers 28-A24559A and 22- A24559B, for cracks in accordance with paragraph 3-11 of Canadair Service Information Circular No. 379-CL44, Issue 3, dated February 23, 1982. If a crack is found in the reinforcing channel, replace the part prior to further flight in accordance with the circular. Terminating action for this inspection consists of replacement of the reinforcing channels with steel reinforcements, Parts Numbers 28-21312-2, -3, -4, and -5 in accordance with paragraphs 3.13 and 3.14 of the Service Information Circular.

3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.

4. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD.

This amendment becomes effective June 6, 1983.

FOOTER: