80-01-02 BRITISH AEROSPACE/SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39-3644. Applies to Concorde Type I airplanes.
To prevent failure of the main landing gear tires or wheels or both resulting from underinflated tire conditions, accomplish the following, or an FAA-approved equivalent:
(a) Before each flight after the effective date of this AD check the tire pressure of each main landing gear tire in accordance with the instructions of Chapter 12.14.32 of the Maintenance Manual as follows:
(1) When the gate stop time is more than 4 hours, verify the tire pressure within 2 hours preceding start of engines.
(2) When the gate stop time is between 3 and 4 hours, verify the tire pressure within the hour preceding the start of engines.
(3) When the gate stop time is 2 to 3 hours verify the tire pressure within 30 minutes preceding the start of engines.
(4) When the gate stop time is less than 2 hours verify the tire pressure within 30 minutes preceding the start of engines and comply with paragraph (c) of this AD.
(b) If as a result of the tire pressure verifications required by paragraph (a)(1), (a)(2) or (a)(3) of this AD, the tire pressure was found to be -
(1) Between 14.6 bars/212 psi and 15 bars/218 psi, no further action required;
(2) From 14.2 bars/206 psi to 14.6 bars/212 psi, reinflate to 15 bars/218 psi;
(3) From 13.4 bars/195 psi to 14.2 bars/206 psi, reinflate to 15 bars/218 psi and record this action for future reference;
(4) From 12.6 bars/183 psi to 13.4 bars/195 psi, replace that wheel and tire and comply with paragraph (e) of this AD; or
(5) Below 12.6 bars/183 psi, replace that wheel and tire and also replace the adjoining wheel and tire and comply with paragraph (e) of this AD.
(c) If as a result of the tire pressure verification required by paragraph (a)(4) of this AD the pressure was found to be -
(1) Above 14.6 bars/212 psi - nofurther action is required;
(2) From 14.2 bars/206 psi to 14.6 bars/212 psi, reinflate the tire to 15 bars/218 psi;
(3) From 12.6 bars/183 psi to 14.2 bars/206 psi, replace that tire and wheel and comply with paragraph (e) of this AD; or
(4) Below 12.6 bars/183 psi, replace that wheel and tire and also replace the adjoining wheel and tire and comply with paragraph (e) of this AD.
(d) Prior to further flight, replace the wheel and tire, and accomplish the "push-in" fuse plug check in accordance with Aerospatiale Campaign Wire 32CW076, Issue 4, if -
(1) The cockpit brake temperature indicator records a temperature above 510C/950F;
(2) A rejected takeoff is executed from a speed over 100 knots, with a brake cooling fan inoperative and the corresponding brake was not deactivated; or
(3) A landing was accomplished with a brake cooling fan inoperative and the corresponding brake was not deactivated.
(e) Perform the non-destructive test, and the "push-in" fuse plug check on any wheel removed from the aircraft as required in paragraph (b), (c), or (d) of this AD, in accordance with Aerospatiale Campaign Wire 32CW076, Issue 4.
(f) Any discrepancies found on the wheels, tires, brakes or on the fuse plugs during the inspections defined above must be reported to the Chief, Aircraft Certification Staff, AEU-100, Federal Aviation Administration, c/o American Embassy, Brussels, Belgium. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.)
(g) An equivalent means of compliance with the requirements of this AD may be used if approved by the Chief, Aircraft Certification Staff, AEU-100, Federal Aviation Administration, c/o American Embassy, Brussels, Belgium.
This supersedes telegraphic AD T79EU11, dated September 10, 1979.
This amendment becomes effective December 26, 1979.