Airworthiness Directive · Amendment 39-17707 · Equipment/furnishings
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2022-06-02. Comply with the one in force.
This AD applies to Airbus Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in any category; all manufacturer serial numbers.
We are superseding Airworthiness Directive (AD) 2010-24-07 for all Airbus Model A318 series airplanes, Model A319 series airplanes, Model A320 series airplanes, and Model A321 series airplanes. AD 2010- 24-07 required repetitive inspections of the 80VU rack lower lateral fittings for damage, repetitive inspections of the 80VU rack lower central support for cracking, and corrective action if necessary. AD 2010-24-07 also specified optional terminating action for the repetitive inspections. This new AD reduces the inspection compliance time, adds an inspection of the upper fittings and shelves of the 80VU rack, and adds airplanes to the applicability. This AD was prompted by reports of worn lower lateral fittings of the 80VU rack. We are issuing this AD to detect and correct damage or cracking of the 80VU fittings and supports, which could lead to possible disconnection of the cable harnesses to one or more computers, and if occurring during a critical phase of flight, could result in reduced control of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
This paragraph restates the requirements of paragraph (g) of AD 2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). Except for Model A318-121 and -122 airplanes, and except for airplanes on which Airbus Modification 34804 has been embodied in production, or on which Airbus Service Bulletins A320-25-1557 and A320-53-1215 have been done in service, prior to the accumulation of 24,000 total flight cycles, or within 500 flight cycles after January 11, 2011 (the effective date of AD 2010-24-07), whichever occurs later: Do a special detailed inspection of the 80VU rack lower lateral fittings for damage (e.g., broken fitting, missing bolts, migrated bushings, material burr, or rack in contact with the fitting) of the 80VU rack lower lateral fittings, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, Revision 02, dated November 5, 2008. Repeat the inspection thereafter at the interval specified in paragraph (g)(1) or (g)(2) of this AD, as applicable. Modifying the 80VU lower lateral fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-25-1557, Revision 02, dated November 5, 2008, terminates the inspection requirements of this paragraph. Doing the initial inspection specified in paragraph (l) of this AD terminates the requirements of this paragraph.
(1) For airplanes on which the 80VU rack lower lateral fittings have not been replaced in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, Revision 02, dated November 5, 2008: Repeat the inspection thereafter at intervals not to exceed 4,500 flight cycles.
(2) For airplanes on which the 80VU rack lower lateral fittings have been replaced in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, Revision 02, dated November 5, 2008: Do the next inspection within 24,000 flight cycles after doing the replacement and repeat the inspection thereafter at intervals not to exceed 4,500 flight cycles.
This paragraph restates the requirements of paragraph (h) of AD 2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010), with new corrective actions. If any damage is found during any inspection required by paragraph (g) of this AD, do all applicable corrective actions (inspection and/or repair), in accordance with the Accomplishment Instructions and timeframes in Airbus Mandatory Service Bulletin A320-25A1555, Revision 02, dated November 5, 2008; or in accordance with and at the time specified in paragraph (q) of this AD. As of the effective date of this AD, if any damage is found, do all applicable corrective actions in accordance with and at the times specified in paragraph (q) of this AD.
This paragraph restates the requirements of paragraph (i) of AD 2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). Except for airplanes on which Airbus Modification 34804 has been embodied in production or on which Airbus Service Bulletins A320-25-1557 and A320-53-1215 have been done in service, prior to the accumulation of 24,000 total flight cycles, or within 500 flight cycles after January 11, 2011 (the effective date of AD 2010-24-07), whichever occurs later: Do a special detailed inspection of the 80VU rack lower central support for cracking, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, Revision 02, dated November 5, 2008. Repeat the inspection thereafter at the interval specified in paragraph (i)(1) or (i)(2) of this AD, as applicable. Replacing the pyramid fitting on the 80VU rack with a new, reinforced fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1215, dated November 5, 2008, terminates the inspection requirements of this paragraph. Doing the initial inspection specified in paragraph (n) of this AD terminates the requirements of this paragraph.
(1) For airplanes on which the 80VU rack lower central support has not been repaired or replaced using Airbus Mandatory Service Bulletin A320-25A1555 or Airbus Service Bulletin A320-25-1557: Repeat the inspection thereafter at the interval specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as applicable.
(i) For airplanes on which the lower central support has accumulated 30,000 total flight cycles or more: At intervals not to exceed 500 flight cycles.
(ii) For airplanes on which the lower central support has accumulated fewer than 30,000 total flight cycles: At intervals not to exceed 4,500 flight cycles, without exceeding 30,750 total flight cycles on the support for the first repetitive inspection.
(2) For airplanes on which the 80VU rack lower central support has been repaired or replaced using Airbus Mandatory Service Bulletin A320-25A1555 or Airbus Service Bulletin A320-25-1557: Do the next inspection within 24,000 flight cycles after the repair or replacement and thereafter repeat the inspection at the interval specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as applicable.
This paragraph restates the requirements of paragraph (j) of AD 2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). If any crack is found during any inspection required by paragraph (i) of this AD: Before further flight, replace the pyramid fitting on the 80VU rack with a new, reinforced fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1215, dated November 5, 2008. Doing this replacement terminates the inspection requirements of paragraph (i) of this AD.
This paragraph restates the requirements of paragraph (k) of AD 2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). Doing the actions specified in paragraphs (k)(1) and (k)(2) of this AD terminates the repetitive inspections required by this AD.
(1) Replacing the pyramid fitting on the 80VU rack with a new, reinforced fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1215, dated November 5, 2008.
(2) Modifying the 80VU lower lateral fittings, in accordance with Airbus Service Bulletin A320-25-1557, Revision 02, dated November 5, 2008.
Except for airplanes on which Airbus Modification 34804 has been embodied in production, or on which the 80VU rack lower lateral support has been modified, as specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25-1557, dated June 14, 2007; Revision 01, dated February 7, 2008; or Revision 02, dated November 5, 2008: At the latest of the applicable times specified in paragraphs (l)(1) through (l)(4) of this AD, do a special detailed (borescope) inspection of the 80VU rack lower lateral fittings for damage (e.g., broken fitting, missing bolts, migrated bushings, material burr, or rack in contact with the fitting), in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, dated February 28, 2012. Repeat the inspection thereafter at intervals not to exceed 500 flight cycles until the terminating action specified in paragraph (k) of this AD is done. Doing the initial inspection specified in this paragraph terminates the requirements of paragraph (g) of this AD.
(1) Before the accumulation of 20,000 total flight cycles from the airplane first flight, or within 750 flight cycles after the effective date of this AD, whichever occurs later, without exceeding 24,000 total flight cycles.
(2) Within 20,000 flight cycles after the most recent repair or replacement of the 80VU rack lower lateral fittings was done, as specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, dated June 24, 2007; Revision 01, dated February 18, 2008; or Revision 02, dated November 5, 2008.
(3) Within 500 flight cycles after the effective date of this AD, without exceeding 4,500 flight cycles after the most recent inspection of the 80VU rack lower lateral fittings was done, as specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, dated June 14, 2007; Revision 01, dated February 18, 2008; or Revision 02, dated November 5, 2008.
(4) Within 500 flight cycles after the effective date of this AD.
If any damage is found during any inspection required by paragraph (l) of this AD: At the applicable time given in paragraph E.(2)., “Accomplishment Timescale,” in Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, dated February 28, 2012, accomplish the applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, dated February 28, 2012; except where this service information specifies to contact Airbus for further instructions, before further flight, contact either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent) for instructions; and do those instructions.
Except for airplanes on which Airbus Modification 34804 has been embodied in production, or on which the 80VU rack lower central support has been modified, as specified in the Accomplishment Instructions of Airbus Service Bulletin A320-53-1215, dated November 5, 2008: At the latest of the applicable times specified in paragraphs (n)(1) through (n)(6) of this AD, do a special detailed (borescope) inspection of the 80VU rack lower central support for cracking, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, dated February 28, 2012. Repeat the inspection thereafter at intervals not to exceed 500 flight cycles until the terminating action specified in paragraph (k) of this AD is done. Doing the initial inspection specified in this paragraph terminates the requirements of paragraph (i) of this AD.
(1) Before the accumulation of 20,000 total flight cycles from the airplane first flight, or within 750 flight cycles after the effective date of this AD, whichever occurs later, without exceeding 24,000 total flight cycles.
(2) Within 20,000 flight cycles after the most recent repair or replacement of the 80VU rack lower central support was done, as specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, dated June 14, 2007; Revision 01, dated February 18, 2008; or Revision 02, dated November 5, 2008.
(3) Within 20,000 flight cycles after modification of the 80VU rack lower central support was done, as specified in the Accomplishment Instructions of Airbus Service Bulletin A320-25-1557, dated June 14, 2007; or Revision 01, dated February 07, 2008.
(4) For airplanes on which, as of the effective date of this AD, the 80VU rack lower central support has accumulated fewer than 30,000 total flight cycles: Within 500 flight cycles after the effective date of this AD, without exceeding 4,500 flight cycles after the most recent inspection of the 80VU rack lower central support was done, as specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, dated June 24, 2007; Revision 01, dated February 18, 2008; or Revision 02, dated November 5, 2008.
(5) For airplanes on which, as of the effective date of this AD, the 80VU rack lower central support has accumulated 30,000 total flight cycles or more: Within 500 flight cycles after the most recent inspection of the 80VU rack lower central support was done, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, dated June 14, 2007; Revision 01, dated February 18, 2008; or Revision 02, dated November 5, 2008.
(6) Within 500 flight cycles after the effective date of this AD.
If any cracking is found during any inspection required by paragraph (n) of this AD: Before further flight do the actions in paragraph (o)(1) or (o)(2) of this AD.
(1) If kits 25A1555A01 thru A05 are available, contact the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent); for instructions and do the repair.
(2) Do the actions specified in paragraph (k)(1) and (k)(2) of this AD.
Concurrently with each special detailed inspection required by paragraphs (l) and (n) of this AD: Do a general visual inspection for damage (cracking or deformation) of the upper fittings and shelves of the 80VU rack, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, dated February 28, 2012. If any damage is found: Before further flight, repair the damage using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or its delegated agent).
For airplanes that have been inspected before the effective date of this AD as specified in Airbus Service Bulletin A320-25A1555, dated June 14, 2007; Airbus Mandatory Service Bulletin A320-25A1555, Revision 01, dated February 18, 2008; or Airbus Mandatory Service Bulletin A320-25A1555, Revision 02, dated November 5, 2008; and on which damage of the fittings was found, except for airplanes specified in paragraph (q)(1) or (q)(2) of this AD: At the applicable time given in paragraph E.(2)., “Accomplishment Timescale,” of Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, dated February 28, 2012, accomplish the applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, dated February 28, 2012, except where this service information specifies to contact Airbus for further instructions, before further flight, contact either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or its delegated agent); for instructions and follow those instructions. Accomplishing the actions required by this paragraph terminates the requirements of paragraph (h) of this AD.
(1) Airplanes on which Airbus Modification 34804 has been embodied in production.
(2) Airplanes on which the terminating action specified in paragraph (k) of this AD has been done.
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.
Aircraft
