{"id":"F2006B01974","name":"AD/A320/85 - Probe Heat Computer","slug":"ad-a320-85-probe-heat-computer","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"repealed","isInForce":false,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":41196,"registerId":"commonwealth-F2006B01974-current","compilationNumber":null,"startDate":"2026-04-01","status":"Repealed","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/A320/85 - Probe Heat Computer","content":"COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n![](image.001.png)  \nAirbus Industrie A319, A320 and A321 Series Aeroplanes\n\nAD/A320/85 Probe Heat Computer 12/97\n\nApplicability: All Airbus Industrie A320 models not having Airbus Industrie modification No.\n\n26403 or Airbus Industrie Service Bulletin A320-30-1036 Revision 1 dated 7 July 1997 incorporated.\n\nRequirement: Unless previously incorporated, modify the wiring between engine interface units one and two with probe heat computer one and three in accordance with Airbus Industrie Service Bulletin A320-30-1036.\n\nNote: DGAC AD 97-203-102(B) refers.\n\nCompliance: Prior to 22 May 1998.\n\nThis airworthiness directive becomes effective on 6 November 1997.\n\nBackground: This AD is intended to prevent a simultaneous loss of heating of probes (CAPT and STBY side) due to a single failure, which will induce erroneous anemometric calculations by the concerned systems whilst operating in freezing conditions.","sortOrder":0}],"analysis":{"kimi_summary":{"_metrics":{"model":"kimi-k2.5","source":"moonshot-batch","completionTokens":1326},"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"The directive maintains its original narrow scope addressing the specific wiring fault in probe heating systems. It has not expanded beyond the original safety issue of preventing simultaneous probe heating failure in freezing conditions."},"complexity_factors":["Single, specific technical requirement with one clear compliance deadline","Limited applicability to one aircraft type and specific unmodified configurations","Only one external technical reference (Airbus Service Bulletin)","No conditional logic, exceptions, or nested provisions","Brief document focused entirely on one identified safety defect"],"plain_english_summary":"This is a **mandatory safety instruction** (called an Airworthiness Directive) for owners and operators of certain Airbus A320 aircraft.\n\n**What it requires:**\nIf you operate an Airbus A320 that hasn't already been modified with Airbus Service Bulletin A320-30-1036, you must rewire the connections between the engine interface units and the probe heat computers. This modification must be completed by **22 May 1998**.\n\n**Why it matters:**\nWithout this fix, a single electrical failure could knock out heating to both the captain's and standby flight probes (sensors) at the same time. In freezing conditions, this would cause ice to build up on these probes, leading to **incorrect airspeed readings** — a serious flight safety risk that could affect the pilots' ability to control the aircraft.\n\n**Who is affected:**\nAll Airbus A320 models that haven't already incorporated Airbus Modification No. 26403 or the specific Service Bulletin dated July 1997."}},"importantCases":[],"_links":{"self":"/api/acts/ad-a320-85-probe-heat-computer","history":"/api/acts/ad-a320-85-probe-heat-computer/history","analysis":"/api/acts/ad-a320-85-probe-heat-computer/analysis","conflicts":"/api/acts/ad-a320-85-probe-heat-computer/conflicts","importantCases":"/api/acts/ad-a320-85-probe-heat-computer/important-cases","documents":"/api/acts/ad-a320-85-probe-heat-computer/documents"}}