AD 2013-14-04 Airworthiness Directives; Airbus Airplanes

Models named: A330-223F, -223, -321, -322, -323. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A330-223F, -223, -321, -322, and -323 airplanes, certificated in any category, all manufacturer serial numbers.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

(1) Within the compliance times specified in table 1 to paragraph (g) of this AD, as applicable to airplane model and utilization, do a torque check to determine if there are any loose or broken forward engine mount bolts (4 positions/engine) on both engines, and repeat that torque check at intervals not to exceed the values defined in table 1 to paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-71-3028, Revision 01, dated February 20, 2012. For the purposes of table 1 to paragraph (g) of this AD, the average flight time (AFT) is defined as a computation of the number of flight hours divided by the number of flight cycles accumulated since last torque check or since the airplane's first flight, as applicable. Table 1 to Paragraph ( g ) of This AD Airplane models Flight cycles accumulated on the effective date of this AD since last torque check performed as specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71-32, or since airplane first flight, as applicable Compliance time Torque check interval (not to exceed) For Model A330-223,-321, -322, and -323 airplanes with AFT more than 132 minutes 0-1,850 Within 2,350 flight cycles since the last torque check as specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71-32, or since airplane first flight, as applicable 2,350 flight cycles or 24,320 flight hours, whichever occurs first. For Model A330-223, -321, -322, and -323 airplanes with AFT more than 132 minutes 1,851-2,700 Within 500 flight cycles after the effective date of this AD without exceeding 2,700 flight cycles since last torque check as specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71-32, or since airplane first flight, as applicable; or within 3 months after the effective date of this AD; whichever occurs later 2,350 flight cycles or 24,320 flight hours, whichever occurs first. For Model A330-321,-322, and -323 airplanes with AFT equal or less than 132 minutes; and for Model A330-321, -322, and -323 airplanes on which the AFT is not calculated on a regular basis 0-1,450 Within 1,950 flight cycles since the last torque check performed as specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71-32, or since airplane first flight, as applicable 1,950 flight cycles or 20,210 flight hours, whichever occurs first. For Model A330-321, -322, and -323 airplanes with AFT equal or less than 132 minutes; and for Model A330-321,-322, and -323 airplanes on which the AFT is not calculated on a regular basis 1,451-2,700 Within 500 flight cycles after the effective date of this AD without exceeding 2,700 flight cycles since last torque check performed as specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71-32, or since airplane first flight, as applicable; or within 3 months after the effective date of this AD; whichever occurs later 1,950 flight cycles or 20,210 flight hours, whichever occurs first. For Model A330-223F airplanes Not applicable Within 2,140 flight cycles or 6,600 flight hours, whichever occurs first since the last torque check performed as specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71-32, or since airplane first flight, as applicable 2,140 flight cycles or 6,600 flight hours, whichever occurs first. (2) If any loose or broken bolt is detected during the check required by paragraph (g)(1) of this AD, before further flight, replace all four forward engine mount bolts and associated nuts, on the engine where the loose or broken bolt was detected, with new bolts and nuts, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-71-3028, Revision 01, dated February 20, 2012. (3) Replacement of bolts and nuts as required by paragraph (g)(2) of this AD is not terminating action for the repetitive torque checks required by paragraph (g)(1) of this AD.

This AD was prompted by fatigue load analysis that determined that certain pylon bolts inspection interval must be reduced. We are issuing this AD to detect and correct loose or broken bolts, which could lead to engine detachment in-flight, and damage to the airplane.

This AD affects AD 2006-16-05, Amendment 39-14705 (71 FR 44185, August 4, 2006).