Airworthiness Directive · Amendment 39-17213 · Periodic inspections
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2016-20-12. Comply with the one in force.
(1) 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 serial numbers.
(2) This AD requires revisions to certain operator maintenance documents to include new actions (e.g., inspections and/or Critical Design Configuration Control Limitations (CDCCLs). Compliance with these actions is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance (AMOC) according to paragraph (l)(1) of this AD. The request should include a description of changes to the required actions that will ensure the continued operational safety of the airplane.
We are superseding an existing airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; and all Model A319, A320, and A321 series airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This new AD requires revising the maintenance program to incorporate revised fuel maintenance and inspection tasks, and adds airplanes to the applicability. This AD was prompted by Airbus issuing more restrictive maintenance requirements and/or airworthiness limitations. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss 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 (f) of AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009). For Model A318-111 and -112 airplanes, and Model A319, A320, and A321 airplanes: Within 3 months after August 28, 2007 (the effective date of AD 2007-15-06, Amendment 39-15135 (72 FR 40222, July 24, 2007)), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A318/A319/A320/A321 ALS Part 5-Fuel Airworthiness Limitations, dated February 28, 2006, as defined in Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005 (approved by the European Aviation Safety Agency (EASA) on March 14, 2006), Section 1, “Maintenance/Inspection Tasks”; or Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 2, dated July 8, 2008 (approved by the EASA on December 19, 2008), Section 1, “Maintenance/Inspection Tasks.” For all tasks identified in Section 1 “Maintenance/Inspection Tasks,” of Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005; or Issue 2, dated July 8, 2008; the initial compliance times start from August 28, 2007 (the effective date of AD 2007-15-06), and the repetitive inspections must be accomplished thereafter at the intervals specified in Section 1, ”Maintenance/Inspection Tasks,” of Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005; or Issue 2, dated July 8, 2008.
Note 1 to paragraph (g) of this AD: Airbus Operator Information Telex (OIT) SE 999.0076/06, dated June 20, 2006, provides guidance on identifying the applicable sections of the Airbus A318/A319/A320/A321 Airplane Maintenance Manual for accomplishing the tasks specified in Section 1 “Maintenance/Inspection Tasks,” of Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005; or Issue 2, dated July 8, 2008.
This paragraph restates the requirements of paragraph (g) of AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009). For Airbus Model A318-111 and -112 airplanes, and Model A319, A320, and A321 airplanes: Within 12 months after August 28, 2007 (the effective date of AD 2007-15-06, Amendment 39-15135 (72 FR 40222, July 24, 2007)), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A318/A319/A320/A321 ALS Part 5-Fuel Airworthiness Limitations, dated February 28, 2006, as defined in Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005 (approved by the EASA on March 14, 2006), Section 2, “Critical Design Configuration Control Limitations”; or Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 2, dated July 8, 2008 (approved by EASA on December 19, 2008), Section 2, “Critical Design Configuration Control Limitations.”
(1) This paragraph restates the requirements of paragraph (h) of AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009). Except as provided by paragraph (l) of this AD: After accomplishing the actions specified in paragraphs (g) and (h) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used.
(2) Notwithstanding any other maintenance or operational requirements, components that have been identified as airworthy or installed on the affected airplanes before the revision of the ALS, as required by paragraphs (g) and (h) of this AD, do not need to be reworked in accordance with the CDCCLs. However, once the ALS has been revised, future maintenance actions on these components must be done in accordance with the CDCCLs.
Within 6 months after the effective date of this AD: Revise the maintenance program to incorporate the new or revised tasks, life limits, and CDCCLs specified in Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010, except as required in paragraph (j)(4) of this AD. The initial compliance times and intervals are stated in this ALS document, except as required in paragraphs (j)(1) through (j)(4) of this AD, or within 6 months after the effective date of this AD, whichever occurs later. For certain tasks, the compliance times depend on the pre-modification and post-modification status of the airplane. Incorporating the requirements of this paragraph terminates the corresponding requirements of paragraphs (g) and (h) of this AD.
(1) For airplanes for which the first flight occurred before August 28, 2007 (the effective date of AD 2007-15-06, Amendment 39-15135 (72 FR 40222, July 24, 2007)), the first accomplishment of Tasks 281800-01-1, Functional Check of Tank Vapour Seal and Vent Drain System; and 281800-02-1, Detailed Inspection of Vapour Seal; must be performed no later than 11 months after the effective date of this AD.
(2) The first accomplishment of Tasks 470000-01-1, Operational Check of Dual Flapper Shutoff Valves (DFSOV), Dual Flapper Check Valves and Nitrogen Enriched Air (NEA) Line for Leaks; 470000-02-1, Operational Check of Both Dual Flapper Check Valves for Leaks; 470000-03-1, Operational Check of Dual Flapper Check Valves for Reverse Flow and NEA Line for Leaks; 470000-04-1, Operational Check of Dual Flapper Check Valves for Reverse Flow; and 470000-05-1, Remove Air Separation Module (ASM) and Return to Vendor for Workshop Check; must be calculated, in accordance with paragraph (j)(2)(i) or (j)(2)(ii) of this AD.
(i) From the airplane first flight for airplanes on which Airbus modification 38062 or 38195 has been embodied in production.
(ii) From the in-service installation of the fuel tank inerting system specified in Airbus Service Bulletin A320-47-1001, Airbus Service Bulletin A320-47-1002, Airbus Service Bulletin A320-47-1003, Airbus Service Bulletin A320-47-1004, Airbus Service Bulletin A320-47-1006, or Airbus Service Bulletin A320-47-1007.
(3) Although Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010, does not refer to Airbus Service Bulletin A320-47-1006 and Airbus Service Bulletin A320-47-1007, the tasks apply as specified in paragraphs (j)(3)(i) through (j)(3)(iv) of this AD.
(i) Tasks 470000-01-1, Operational Check of DFSOV, Dual Flapper Check Valves and NEA Line for Leaks; and 470000-02-1, Operational Check of Both Dual Flapper Check Valves for leaks; apply to airplanes that have previously accomplished the actions specified in Airbus Service Bulletin A320-47-1007.
(ii) Task 470000-03-1, Operational Check of Dual Flapper Check Valves for Reverse Flow and NEA Line for Leaks, applies to airplanes that have previously accomplished the actions specified in Airbus Service Bulletin A320-47-1006, and that have not accomplished the actions specified in Airbus Service Bulletin A320-47-1007.
(iii) Task 470000-04-1, Operational Check of Dual Flapper Check Valves for Reverse Flow, applies to airplanes in post-modification 38195 configuration and that have not accomplished the actions specified in Airbus Service Bulletin A320-47-1007.
(iv) Task 470000-05-1, Remove ASM and return to Vendor for Workshop Check, applies to airplanes that have previously accomplished the actions specified in Airbus Service Bulletin A320-47-1007, and are in pre-modification 151529 configuration.
(4) Replace each ASM identified in table 1 to paragraph (g)(4) of this AD in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or its delegated agent). The compliance time for the replacement is before the accumulation of 27,000 total flight hours (component time)—i.e., the life limitation.
Note 2 to paragraph (g)(4) of this AD: Airbus A318/A319/A320/A321 Aircraft Maintenance Manual Task 47-10-43-920-001-A, Air Separation Module Replacement, is an additional source of guidance for accomplishment of the removal and replacement of the ASM.
| ASM Part Number— | Affected Airplane Configuration— |
|---|---|
| 2060017-101 | Post-modification 38062, or Post-Airbus Service Bulletin A320-47-1002, or Post-Airbus Service Bulletin A320-47-1004, or Post-Airbus Service Bulletin A320-47-1007 |
| 2060017-102 | Post-modification 152033, or Post-Airbus Service Bulletin A320-47-1011 |
After accomplishing the revisions required by paragraph (j) of this AD, no alternative actions (e.g., inspections), intervals, and/or CDCCLs may be used other than those specified in Airbus A318/A319/A320/A321 ALS Part 5-Fuel Airworthiness Limitations, dated February 28, 2006, as defined in Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010, unless the actions, intervals, and/or CDCCLs are approved as an AMOC in accordance with the procedures specified in paragraph (l)(1) 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.
Aircraft
