AD 68-01-06 R1

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AD Number:
68-01-06 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CANADAIR Model CL-44D4 Series Airplanes
Subject:
Main Landing Gear Bogie Beam
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/05/1988
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Superseded AD: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Superseded By: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: 68-01-06 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5989

AD NUMBER:   68-01-06 R1

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

ACTION:  

SUMMARY:  

DATES:   Effective September 5, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
68-01-06 R1 CANADAIR: Amendment 39-537 as amended by Amendment 39-5989. Applies to all Model CL-44D4 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished.

To prevent failure of the main landing gear during landing or takeoff due to cracks in the main landing gear bogie beam, accomplish the following:

A. Within the next 20 landings after the effective date of this AD, and thereafter at intervals not to exceed 20 landings, perform a visual inspection of the left and right main landing gear bogie beam, P/N 44-87574, for cracks, in accordance with paragraph 2.A.(1) of Canadair Service Bulletin 493-CL44, dated February 29, 1988.

B. At intervals not to exceed 500 landings or 12 months, whichever occurs first, perform the inspection and modification, if necessary, in accordance with paragraphs 2.A.(2), 2.A.(3), 2.A.(4) and 2.A.(5) of Canadair Service Bulletin 493-CL44, dated February 29, 1988.

C. Any structure found to be cracked as a result of the inspections required by paragraph A. or B., above, must be replaced, prior to further flight, with an airworthy part or an FAA-approved equivalent part.

1. Replacement parts must be inspected prior to installation, in accordance with paragraph 2.A.(3) of Canadair Service Bulletin 493-CL44, dated February 29, 1988.

2. Replacement parts must be repetitively inspected in accordance with paragraphs A. and B., above.

D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region.

E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Canadair, LTD., Commercial Aircraft Technical Services, Box 6087, Station A, Montreal, Quebec H3C 3G9, Canada. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York.

This action amends AD 68-01-06, Amendment 39-537.

This amendment, 39-5989, becomes effective September 5, 1988.

FOOTER: