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 Federal Register Information
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
AD 64-02-04
Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft
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AGENCY: Federal Aviation Administration, DOT
DATES: Effective January 23, 1964.
Regulatory Information
64-02-04 CANADAIR: Amdt. 677 Part 507 Federal Register January 23, 1964. Applies to all Model CL-44D4 aircraft.
Compliance required as indicated.
As a result of an incident indicating binding of a sealed coupling due to rotation of an eccentrically bored nylatron bushing in an eccentrically bored housing P/N 44A53941-951, accomplish the following inspection within 25 hours' time in service after the effective date of this AD unless already accomplished.
(a) Inspect all 14 control system couplings P/N 44A53940 to determine if housing P/N 44A53941-951 is being utilized (housing P/N impression is stamped on unpressurized face of mounting flange).
(b) If housing P/N 44A53941-951 is being utilized, accomplish one of the following before further flight.
(1) Replace housing P/N 44A53941-951 with housing P/N 44A53941 with no dash number modified per Canadair Service Bulletin No. 304, Revision B, dated July 11, 1963, or an equivalent approved by Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
(2) Rework housing P/N 44A53941-951 as follows:
(i) Remove nylatron or steel bushing from housing P/N 44A53941- 951;
(ii) Rebore the hole for bushing to 0.750 plus 0.000 minus 0.001 inch-diameter and make bushing hole concentric within 0.001 inch with the hole bore for the bearings;
(iii) Reinstall special nylatron bushing which will provide 0.0010 to 0.0025 inch interference fit with housing bore;
(iv) Finish bore inner diameter of nylatron bushing 0.629 plus 0.001 minus 0.000 inch and make hole in the bushing concentric within 0.001 inch with the hole bore for bearings; and
(v) Reidentify housing as P/N 44A53941-952.
(3) Remove nylatron or steel bushing from housing P/N 44A53941-951 for interim aircraft operation. However, housing shall be replaced or reworked in accordance with either (b)(1) or (b)(2) within 100 hours' time in service after the removal of the bushing. Couplings that are reworked or replaced after this interim operation shall be thoroughly cleaned and lubricated before reinstallation.
(Canadair Service Bulletin No. 304, Revision B, dated July 11, 1963, and Canadair Limited telegram dated January 7, 1964, to Seaboard World Airlines, Flying Tigers Airlines and Slick Airways covers this same subject.)
This directive effective January 23, 1964.
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