Airworthiness Directive · Amendment 39-19140 · Fire protection
ATR-GIE Avions de Transport Régional Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category.
(1) ATR—GIE Avions de Transport Régional Model ATR42-500 airplanes; manufacturer serial number (MSN) 859, and MSNs 1001 through 1010 inclusive.
(2) ATR—GIE Avions de Transport Régional Model ATR72-212A airplanes; MSN 988 and 989; MSNs 993 through 1000 inclusive, except MSN 996; and MSNs 1020 through 1142 inclusive, except MSNs 1071, 1135, 1139, 1140, and 1141.
We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR 42-500 airplanes and Model ATR 72-212A airplanes. This AD requires a one-time inspection for damage of the engine fire extinguishing pipes and incorrect pipe installation, and corrective actions if necessary. This AD was prompted by a report of damage to an engine fire extinguishing pipe due to chafing between the pipe and a fastener assembly; the chafing occurred as a result of incorrect installation of the pipe. We are issuing this AD to address the unsafe condition on these products.
Within 150 flight hours or 30 days, whichever occurs first after the effective date of this AD, accomplish a one-time inspection for damage of the left-hand (LH) and right-hand (RH) engine fire extinguishing pipes, in accordance with the Accomplishment Instructions of ATR Service Bulletin ATR42-26-0031, dated April 30, 2014; or ATR Service Bulletin ATR72-26-1027, dated April 30, 2014; as applicable.
If, during the inspection required by paragraph (g) of this AD, any damage is detected on an engine fire extinguishing pipe, before further flight, remove the damaged pipe, measure the maximum wear depth in accordance with the Accomplishment Instructions of ATR Service Bulletin ATR42-26-0031, dated April 30, 2014; or ATR Service Bulletin ATR72-26-1027, dated April 30, 2014; as applicable.
If, during a measurement required by paragraph (h) of this AD, a depth of wear greater than 0.5 mm (0.0197 inch) is detected, before further flight, accomplish the actions specified by paragraphs (i)(1), (i)(2), and (i)(3) of this AD, in accordance with the Accomplishment Instructions of ATR Service Bulletin ATR42-26-0031, dated April 30, 2014; or ATR Service Bulletin ATR72-26-1027, dated April 30, 2014; as applicable.
(1) Replace the damaged pipe with a new engine fire extinguishing pipe.
(2) Inspect the LH and RH flap parts (flap fasteners, flap arms, hinge flaps) at rib 4 for damage; and, depending on the findings, accomplish the applicable corrective actions, except, where ATR Service Bulletins ATR42-26-0031 and ATR72-26-1027, both dated April 30, 2014, specify to contact ATR for appropriate action, before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (n)(2) of this AD.
(3) Accomplish a functional test of the engine fire extinguishing system. If the part fails the test, before further flight, do corrective actions, repeat the test, and do applicable corrective actions until the part passes the test.
If, during a measurement required by paragraph (h) of this AD, a depth of wear less than, or equal to, 0.5 mm (0.0197 inch) is detected, before further flight, accomplish the actions required by paragraphs (j)(1), (j)(2), and (j)(3) of this AD in accordance with the Accomplishment Instructions of ATR Service Bulletin ATR42-26-0031, dated April 30, 2014; or ATR Service Bulletin ATR72-26-1027, dated April 30, 2014; as applicable.
(1) Do the actions specified by either paragraph (j)(1)(i) or (j)(1)(ii) of this AD.
(i) Replace the damaged pipe with a new engine fire extinguishing pipe.
(ii) Re-install the damaged pipe correctly, and, within 30 days after the inspection as required by paragraph (g) of this AD, replace the damaged pipe with a new engine fire extinguishing pipe.
(2) Inspect the LH and RH flap parts (flap fasteners, flap arms, hinge flaps) at rib 4 for damage; and, depending on the findings, accomplish all applicable corrective actions before further flight, except, where ATR Service Bulletins ATR42-26-0031 and ATR72-26-1027, both dated April 30, 2014, specify to contact ATR for appropriate action, before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (n)(2) of this AD.
(3) Accomplish a functional test of the engine fire extinguishing system. If the part fails the test, before further flight, do corrective actions, repeat the test, and do applicable corrective actions until the part passes the test.
Within 30 days after the replacement specified by paragraph (h) of this AD, unless already accomplished as required by paragraph (i)(1) or (j)(1) of this AD, as applicable, replace the damaged fire extinguisher pipe in accordance with the instructions of ATR Service Bulletin ATR42-26-0031, dated April 30, 2014; or ATR Service Bulletin ATR72-26-1027, dated April 30, 2014; as applicable, and, concurrently, accomplish the actions specified by paragraphs (j)(2) and (j)(3) of this AD.
If, during the inspection required by paragraph (g) of this AD, no damage is detected, before further flight, verify the correct installation of the extinguishing pipes, in accordance with the Accomplishment Instructions of ATR Service Bulletins ATR42-26-0031 or ATR72-26-1027, both dated April 30, 2014, as applicable. If any engine fire extinguishing pipe is found incorrectly installed, before further flight, re-install the pipe correctly and accomplish a functional test of the engine fire extinguishing system in accordance with the Accomplishment Instructions of ATR Service Bulletin ATR42-26-0031, dated April 30, 2014; or ATR Service Bulletin ATR72-26-1027, dated April 30, 2014; as applicable. If the part fails the test, before further flight, do corrective actions, repeat the test, and do applicable corrective actions until the part passes the test.
If, during any inspection specified by paragraph (i)(2) or (j)(2) of this AD, as applicable, any damage is detected on flap arms or hinge flaps that is determined to be beyond the defined limits indicated in ATR Structural Repair Manual (SRM) 511010-01-001-A01, dated October 1, 2014, before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (n)(2) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
