AD 83-07-51 R1

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AD Number:
83-07-51 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CANADAIR Model CL-600-1A11 and CL-600-2A12 Airplanes
Subject:
Flap Vane Support Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/05/1984
Make:
Bombardier Inc.
Model:
CL-600-1A11 (CL-600) | CL-600-2A12 (CL-601) | CL-600-2B16 (CL-601-3A) | CL-600-2B16 (CL-601-3R)
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Superseded AD: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Superseded By: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: 83-07-51 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4874

AD NUMBER:   83-07-51 R1

SUBJECT HEADING:   Airworthiness Directives; CANADAIR Model CL-600-1A11 and CL-600-2A12 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective June 5, 1984.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   83-07-51 R1 CANADAIR: Amendment 39-4874. Applies to Model CL-600-1A11 (CL-600) and CL-600-2A12 (CL-601) airplanes certificated in all categories. Compliance is required as indicated on all airplanes with 150 hours or more total time in service. To prevent failure of the flap vane support assembly, P/N 600-14250-14, accomplish the following, unless previously accomplished:

A. Prior to further flight, except for a flaps up ferry flight, remove the six (three per side) inboard flap vane support beam assemblies, P/N 600-14250-14, and perform a dye penetrant inspection of the beam assemblies in accordance with Canadair Alert Service Bulletin A600-0357, Revision 1, dated June 17, 1983 (CL-600); or A601-0010, Revision 1, dated June 17, 1983 (CL-601). If no cracks are found, repeat the inspection at intervals not to exceed 50 hours time in service.

B. If cracks are found in one beam assembly, replace all six assemblies with new parts of the same part number prior to further flight. Reinspect as noted in paragraph A., above, after the accumulation of 150 additional hours time in service.

C. If no cracks are found in any beam assembly, insert a NOTE in the "Flaps Extended Speed" paragraph of the Limitations Section of the Airplane Flight Manual to read: "Maximum Speed with Flaps 45 degrees, 160 KIAS."

D. Post a placard on the left and right hand instrument panels to read: "Maximum Speed with Flaps 45 degrees, 160 KIAS."

E. The repetitive inspections required by this AD and the flight manual/flap placard speed restrictions given in paragraphs C. and D., above, may be terminated upon installation of modified beam and trunnion assemblies in accordance with Parts C and D of the Service Bulletin.

F. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region.

G. 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 5, 1984, and was effective earlier to all recipients of Telegraphic AD T83-07-51 dated April 6, 1983.

FOOTER: