AD 77-17-01

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AD Number:
77-17-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CANADAIR MODELS CL-44D4 and CL-44J Airplanes
Subject:
Structural Integrity
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/18/1977
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Superseded AD: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Superseded By: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: 77-17-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3007

AD NUMBER:   77-17-01

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

ACTION:  

SUMMARY:  

DATES:   Effective August 18, 1977.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
77-17-01 CANADAIR: Amendment 39-3007. Applies to all CL-44D4 and CL-44J airplanes, certificated in all categories, that have not been altered in accordance with Canadair Service Information Circular No. 151-CL44, Issue 3, dated October 26, 1976, or with an FAA- approved equivalent alteration.

Compliance required as indicated.

(a) To ensure the structural integrity and prevent failure of the following nose landing gear upper radius rods, accomplish the inspection in (1).

Upper Radius Rod
Subassembly
	Upper Radius Rod

Item 1. 44-85045 LH Assembly Employs	44-85084 LH Rod
Item 2. 44-85045-1 RH " "	44-85084-1 RH Rod
Item 3. 44-85045-1000 LH " "	44-85084-2 LH Rod

(1) For parts which have accumulated 1175 or more landings on the effective date of this airworthiness directive, inspect Items 1, 2, and 3 within the next 75 landings by a dye penetrant, eddy current, or ultrasonic method in accordance with the "Inspection Data" and "Inspection Procedure" sections of Canadair Service Information Circular No. 151-CL44, Issue 3, dated October 26, 1976, or with an FAA-approved equivalent inspection.

(2) For parts which have not accumulated 1175 landings on the effective date of this airworthiness directive, accomplish the inspection in (a)(1) before attaining 1250 landings.

(b) Repeat inspections in (a)(1) at intervals not to exceed:

(1) 60 landings for non-reworked parts Item 1 and 3

(2) 200 landings for non-reworked part Item 2

(3) 30 landings for reworked parts Item 1, 2, and 3

(c) Replace cracked parts with new parts of the same part number or with approved equivalent parts, or rework cracked parts to the limitations specified in "Rework Instruction" in Canadair Service Information Circular No. 151-CL44, Issue 3, dated October 26, 1976, or with an approved equivalent procedure.

(d) Replace parts reworked to the maximum limits, specified in "Rework Instruction" in the above Service Information Circular, that have attained an additional 3000 landings from the time of such rework, or when cracks are again detected, whichever occurs first, with new parts of the same part number or with approved equivalent parts.

(e) Equivalent inspections/procedures and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

(f) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection times specified in this AD.

This amendment is effective August 18, 1977.

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