AD 65-04-03

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AD Number:
65-04-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft
Subject:
Elevator Antiflutter Gear Box Strut
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/04/1965
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Superseded AD: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Superseded By: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: 65-04-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-29

AD NUMBER:   65-04-03

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

ACTION:  

SUMMARY:  

DATES:   Effective February 4, 1965.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
65-04-03 CANADAIR: Amdt. 39-29 Part 39 Federal Register February 4, 1965. Applies to Model CL-44D4 aircraft.

Compliance required as indicated.

To prevent further failures of the elevator antiflutter gear box strut that could result in punctured elevator ribs or limited elevator travel, accomplish the following:

(a) For aircraft having shafts P/N's 44A167729-4 and 44A167729-6 in the elevator antiflutter gear box strut assemblies with less than 5,400 hours' time in service on the effective date of this AD, comply with (c) prior to the accumulation of 5,450 hours' time in service, unless already accomplished within the last 250 hours' time in service, and at intervals thereafter not to exceed 300 hours' time in service from the last inspection.

(b) For aircraft having shafts P/N's 44A167729-4 and 44A167729-6 in the elevator antiflutter gear box strut assemblies with 5,400 or more hours' time in service on the effective date of this AD, comply with (c) within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 250 hours' time in service, and at intervals thereafter not to exceed 300 hours' time in service from the last inspection.

(c) Remove the elevator control spring loaded strut assemblies, P/N's 44A167734-2 and 44A167734-6 and disassemble the shaft assemblies and inspect the shafts, P/N's 44A167729- 4 and 44A167729-6 for cracks using dye penetrant in conjunction with at least a 10-power glass or an FAA-approved equivalent.

NOTE - When inspecting the shafts, particular attention should be directed at the location of the washer, P/N 44A28833.

(d) Replace cracked parts with a new part of the same part number or an FAA- approved equivalent before further flight, except that the aircraft may be flown in accordance with the provisions of FAR 21.197 to the base where the repairs are to be accomplished.

(e) Replacement shafts shall be inspected for cracks in accordance with (c) within 5,400 hours' time in service, and at intervals thereafter not to exceed 300 hours' time in service, from the last inspection.

(f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.

This directive effective February 4, 1965.

FOOTER: