AD 63-03-02

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AD Number:
63-03-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft
Subject:
Rudder Balance Weight
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/06/1963
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Superseded AD: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Superseded By: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: 63-03-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   63-03-02

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

ACTION:  

SUMMARY:  

DATES:   Effective February 6, 1963.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
63-03-02 CANADAIR: Amdt. 533 Part 507 Federal Register February 6, 1963. Applies to all Model CL-44D4 aircraft.

Compliance required as indicated.

As a result of failure of a riveted rudder lower balance weight, the following must be accomplished:

(a) Prior to each departure from the principal maintenance base, inspect the rudder bottom closing rib for any indication of a balance weight becoming detached and dropping on to the rib. If so found, repair per (c) prior to further flight.

(b) Within the next 35 hours' time in service after the effective date of this AD, unless already accomplished, inspect the rivet attachment of the two weights (P/N 28-21250-16) to the bottom rudder balance weight assembly (P/N 28-21250-14). There are five 1/8-inch rivets per weight, a total of ten for the entire assembly. If any looseness or failure of the rivets is found, replace all rivets with bolts in accordance with (c).

(c) Within the next 250 hours' time in service after the effective date of this AD, replace the ten 1/8-inch rivets referred to in (b) with AN 509-10R-30 bolts, AN 960-10 washers and NAS 679A3W lock nuts. This requires countersinking the aft face of the P/N 28-21250-14 assembly to accommodate the bolt heads. When this modification has been accomplished, the inspection in (a) may be discontinued.

(Canadair Service Information Circular 262-CL44D4 covers this subject.)

This directive effective February 6, 1963.

FOOTER: