AD 2017-10-18 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.

Comply with this AD within the compliance times specified, unless already done.

(1) At the applicable compliance time specified in table 1 to paragraph (g)(1) of this AD, do a torque check to determine if there are any loose or broken forward engine mount bolts (4 positions/engine) on both engines, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-71-3028, Revision 02, dated August 31, 2015. Repeat the torque check at the applicable time intervals not to exceed the values specified in table 1 to paragraph (g)(1) of this AD. For the purposes 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 the most recent torque check or since the airplane's first flight, as applicable. Accomplishment of the initial torque check required by this paragraph terminates the requirements of AD 2013-14-04. Table 1 to Paragraph ( g )(1) of This AD Airplane models Flight cycles accumulated as of December 19, 2013 (the effective date of AD 2013-14-04), since last torque check specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71-32 or since airplane's first flight, as applicable Compliance time Torque check interval (not to exceed) Model A330-321, -322, and -323 airplanes with AFT more than 132 minutes; and Model A330-223 airplanes 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's first flight, as applicable 2,350 flight cycles or 24,320 flight hours, whichever occurs first. Model A330-321, -322, and -323 airplanes with AFT more than 132 minutes; and Model A330-223 airplanes 1,851-2,700 Within 500 flight cycles after December 19, 2013 (the effective date of AD 2013-14-04), 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's first flight, as applicable; or within 3 months after December 19, 2013; whichever occurs later 2,350 flight cycles or 24,320 flight hours, whichever occurs first. Model A330-321, -322, and -323 airplanes with AFT 132 minutes or less; and 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's first flight, as applicable 1,950 flight cycles or 20,210 flight hours, whichever occurs first. Model A330-321, -322, and -323 airplanes with AFT 132 minutes or less; and 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 December 19, 2013 (the effective date of AD 2013-14-04), without exceeding 2,700 flight cycles since last torque check performed as specified in Pratt & Whitney Alert Service Bulletin PW4-100-A71-32, or since airplane's first flight, as applicable; or within 3 months after December 19, 2013; whichever occurs later 1,950 flight cycles or 20,210 flight hours, whichever occurs first. Model A330-223F airplanes Any 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's 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, do the actions specified by paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-71-3028, Revision 02, dated August 31, 2015; except, where the service information specifies to contact the manufacturer for further corrective actions, before further flight contact the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA); to obtain applicable corrective action instructions approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA; and accomplish the applicable corrective actions within the compliance time specified in those instructions. (i) 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. (ii) Do nondestructive inspections of the forward mount assembly for damage including cracks, dents, nicks, and scratches, and do all applicable corrective actions. (3) Replacement of bolts and nuts as required by paragraph (g)(2)(i) 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 the need for certain reduced inspection intervals and updated torque values of the forward engine mount pylon bolts. 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) (“AD 2006-16-05”); and AD 2013-14-04, Amendment 39-17509 (78 FR 68352, November 14, 2013) (“AD 2013-14-04”).