AD/CESSNA 180/90 - Fuel Line Chafing

The directive introduces several technical concepts that are central to understanding its operation. The ground power receptacle is an electrical socket mounted on the firewall that allows an external ground power unit to supply electricity to the aircraft's electrical system, typically for starting or ground maintenance. When mounted on the firewall and connected via a cable to the forward ground power relay and then to the starter relay, that cable runs in proximity to the fuel strainer control cable and the fuel line between the auxiliary and engine-driven fuel pumps. The forward ground power relay is an electrically operated switch that controls the flow of power from the receptacle to the starter relay. The starter relay is a high-current relay that engages the starter motor. The fuel strainer control cable is a mechanical cable used to operate the fuel strainer drain. The auxiliary electric fuel pump is an electrically driven pump that supplements fuel pressure during certain phases of flight, while the engine-driven fuel pump is a mechanical pump driven by the engine. The risk identified is that the electrical cable can chafe against the metal sheath of the fuel strainer cable or the fuel line itself, causing a short circuit. The short can weld the fuel strainer cable to the firewall and generate enough heat to burn through the fuel line, resulting in a fuel-fed fire. The concept of chafing refers to wear caused by repeated rubbing contact. The directive sets a threshold for chafing severity: if chafing is at or beyond limits defined in the service bulletin, the fuel line must be replaced and the electrical cable removed; otherwise, only adjustment and repositioning are required. The directive also uses the concept of an Alternate Method of Compliance (AMOC), a mechanism by which the FAA may approve a different means of achieving the same safety outcome, allowing later revisions of the service bulletin to be accepted. The placard requirement uses standardised formatting (red letters on white background, red border, 3mm minimum height) to ensure the warning is conspicuous and enduring. The directive references FAA AD 2007-09-01 Amdt 39-15031, which is the United States equivalent directive that prompted this Australian AD.

The directive applies directly to the registered owners and operators of any Cessna Model 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, or 182R aeroplane of any serial number, provided two conditions are met: first, the aeroplane has been modified by installation of Air Plains Services Corporation STC SA00152WI; and second, the aeroplane has a ground power receptacle mounted on the firewall, referred to as a forward ground power receptacle. This is a narrow but concrete population. It excludes all Cessna 182 models not listed, all Cessna 180 models (despite the AD's title referencing the 180 and Wren 460, the applicability table only covers 182H through 182R), and any aircraft without the specific Air Plains STC or without a firewall-mounted ground power receptacle. For aircraft that meet both conditions, the directives are mandatory and must be complied with regardless of whether the aircraft is flown commercially or privately, whether it is registered in Australia or elsewhere if it is operated under an Australian airworthiness certificate. The directive imposes obligations on maintenance organisations, licensed aircraft maintenance engineers (LAMEs), and the persons responsible for continuing airworthiness. The compliance actions require access to the service bulletin, the specified replacement hose (part number AE3663161G0190 or FAA-approved equivalent), and technical skill to disconnect or remove electrical cables, reposition cables, adjust fittings, and fabricate a placard. The directive also indirectly affects Air Plains Services Corporation as the STC holder, because the directive effectively imposes limitations on the approved design: if the STC is installed on an aircraft with a forward ground power receptacle, the STC cannot be operated as designed without this AD being complied with. The directive may affect the resale value of affected aircraft, particularly if the replacement hose is difficult to source or if the permanent removal of the ground power cable reduces operational convenience. The compliance timeframe of approximately two weeks from the effective date imposes a concentrated burden on a small group of owners.

The directive creates six specific duties with staggered compliance dates. First, the registered operator or owner must remove power to the ground power electrical cable by either disconnecting the cable at the forward ground power relay and the starter relay, or removing the cable entirely between those two relays. This action must be completed before 12 May 2007. Second, before further flight after that power removal, the operator must fabricate and install a placard as close as possible to the forward ground power receptacle, using red letters at least 3mm high on a white background with a red border, bearing the words "Ground Power Receptacle is Inoperative". Third, before 12 May 2007, the operator must reposition the fuel strainer cable in accordance with the mandatory service bulletin. Fourth, before 12 May 2007, the operator must visually inspect the fuel line from the auxiliary electric fuel pump to the engine-driven fuel pump for chafing. Fifth, if chafing at or beyond the service bulletin's limits is found during that inspection, the operator must replace the fuel line with a new hose part number AE3663161G0190 (or FAA-approved equivalent) and must also remove the electrical cable per Requirement 1.b before further flight. Sixth, before 12 May 2007, the operator must adjust the position of the fuel line fitting at the engine-driven fuel pump in accordance with the service bulletin. The rights conferred are limited. The operator has the right to use an FAA-approved equivalent part for the replacement hose, and to use a later revision of the service bulletin provided that revision has been approved by the FAA as an AMOC to FAA AD 2007-09-01. There is an implied right to choose between disconnection or removal of the cable for Requirement 1, but if chafing is found, removal is mandatory under Requirement 5. The operator also has the right to have compliance carried out by a licensed maintenance organisation, and to document compliance in the aircraft's logbook or maintenance records. The directive does not grant an extension or waiver from CASA; any deviation would require a separate approval from CASA under the CASR.

This directive does not itself prescribe monetary penalties, imprisonment periods, or specific enforcement actions. Instead, it operates within the broader framework of the Civil Aviation Act 1988 and the Civil Aviation Safety Regulations (CASR). Breaching an airworthiness directive is a breach of the conditions under which the aircraft's certificate of airworthiness or registration is issued. Under regulation 42.10 of CASR, a person who operates an aircraft that does not comply with an applicable AD may be subject to civil penalty proceedings, which can result in fines of up to 200 penalty units for an individual or 1,000 penalty units for a body corporate (as adjusted over time; at 2007 levels a penalty unit was $110). Alternatively, the matter could be dealt with as an offence under section 20A of the Civil Aviation Act, which carries penalties of up to two years imprisonment for reckless conduct endangering safety. In practice, enforcement is typically graduated: CASA may issue a direction to ground the aircraft, require the owner to show cause why enforcement action should not be taken, or issue an infringement notice with a fixed penalty. Non-compliance also exposes the operator to civil liability if an incident occurs: if the condition the AD was designed to prevent (engine compartment fire) materialises and the AD was not complied with, that would be strong evidence of negligence. Insurers may also deny cover for damage or liability if the aircraft was operated in breach of an AD. The directive's compliance dates are absolute: failure to meet the 12 May 2007 deadline for the first set of requirements would have rendered the aircraft non-airworthy for any flight after that date. The enforcement risk is highest for owners who continue to fly the aircraft without the placard or without completing the inspection and adjustment, because the risk of fire is immediate and the required actions are simple.

This Airworthiness Directive is a legislative instrument issued under the Civil Aviation Act 1988 and the Civil Aviation Safety Regulations (CASR). It takes precedence over the normal maintenance standards that would otherwise apply to the aircraft under Part 43 of CASR, because a directive imposes mandatory modifications, inspections, or operating limitations that supersede any less restrictive continuing airworthiness instructions. For an aircraft that is type-certificated in the United States and operated under an Australian certificate of airworthiness, the directive effectively adopts the corrective actions of FAA AD 2007-09-01 and the mandatory service bulletin referenced therein. This means that compliance with the FAA AD alone may not be recognised as compliance with the Australian directive unless the actions performed match the Australian requirements exactly. The note in the directive states that later revisions of the service bulletin are acceptable if approved as an AMOC to the FAA AD, but it does not say that a later revision without AMOC is acceptable. Therefore, strict adherence to the March 2007 version of the service bulletin, or a later AMOC-approved version, is required. The directive also interacts with the conditions of the Supplemental Type Certificate SA00152WI. The STC would have been approved as an alteration to the type design, but this AD effectively prohibits operation of the STC in its original configuration because the ground power receptacle, if mounted on the firewall, must be rendered inoperative. This creates an inconsistency: the STC permits the installation, but the AD requires the receptacle's power cable to be disconnected or removed. An owner who wishes to keep the ground power receptacle functional would need to relocate it (which would be a further modification requiring an approval, not covered by this AD). The directive also interacts with insurance contracts: many aviation insurance policies require that the aircraft be maintained in an airworthy condition and in compliance with all applicable ADs. Failure to comply could void cover. For aircraft operated under the Civil Aviation Regulations 1988 (now mostly superseded by CASR), the AD would have been enforceable under the older regulatory framework as well. The directive does not purport to override workplace health and safety laws, but the actions required (working on electrical systems and fuel lines) are themselves subject to those laws.

The source document provides no amendment history on its face. It is a single Airworthiness Directive numbered AD/CESSNA 180/90, amendment 6/2007 DM, issued on 23 April 2007 and effective 27 April 2007. The directive's note references FAA AD 2007-09-01 Amdt 39-15031, which is a specific amendment number for the corresponding FAA directive. The directive itself says that later revisions of the mandatory service bulletin APS-07-01-01, if approved by the FAA as an AMOC to the FAA AD, are acceptable for compliance with the equivalent requirements of this Australian directive. This implies that the service bulletin may be revised over time, and that the directive operates with a built-in mechanism to accept those revisions without needing to amend the AD itself, provided the FAA grants AMOC approval. However, the directive does not automatically accept all later revisions of the service bulletin; only those with explicit AMOC approval. The directive also does not state that it has itself been amended after its issue date. Whether this directive has since been superseded or withdrawn is not disclosed in the source text. Users must check the current CASA website or the CASA Airworthiness Directives database to determine if a later AD has replaced it, or if the aircraft type has been withdrawn from service or otherwise removed from applicability. The directive's age (2007) means it is likely still in force unless a subsequent AD specifically supersedes it. It is common for ADs on ageing aircraft types to remain in force indefinitely, though compliance may have been achieved on all affected aircraft over time. No amendment history is provided within the document itself, so the reader cannot assume any changes have been made.

The source document mentions no litigation. No cases, court decisions, or tribunal rulings are cited in the directive. Given that the directive is a technical corrective measure for a small subset of aircraft, and that compliance with airworthiness directives is typically uncontested, there is no reason to expect published litigation directly concerning this specific AD. However, the underlying legal framework for enforcement of airworthiness directives under the Civil Aviation Act 1988 has been the subject of proceedings in the Administrative Appeals Tribunal and the Federal Court in other contexts. For example, in matters where CASA has grounded an aircraft for non-compliance with an AD, owners have sought review. The directive's requirement to remove or disconnect a ground power cable and install a placard is a minor imposition compared to structural modifications, so it is unlikely to have provoked litigation. The background reference to the NTSB preliminary report indicates that the FAA AD was based on an accident investigation, but that investigation is a fact-finding process, not litigation. No subsequent civil suits arising from the subject incident are mentioned. The directive itself does not create a private right of action; any litigation arising from non-compliance would be initiated by CASA as an enforcement action, and such cases are rarely reported in detail because they are often concluded by consent or penalty orders. Therefore, the litigation history is effectively nil. The researcher should not assume that any cases exist; the source does not support such an inference.

Several provisions could trap an unwary operator. First, the directive splits compliance between two dates: before 12 May 2007 for Requirements 1, 3, 4 and 6, and before further flight for Requirements 2 and 5. An operator who completes Requirement 1 (disconnect or remove the cable) on, say, 11 May but does not install the placard before the next flight would be in breach before that flight, even though the major work is done. The placard must be fabricated and installed before the aircraft moves. Second, the placard specifications are strict: red letters at least 3mm high on a white background with a red border, and the exact wording "Ground Power Receptacle is Inoperative". A placard with smaller text, different colours, or any additional words would not comply. Third, the directive allows the operator to choose between disconnecting the cable (Requirement 1.a) or removing it (Requirement 1.b), but if chafing is found during the inspection, Requirement 5 mandates removal (1.b) and removes the option to merely disconnect. An operator who initially chose to disconnect (perhaps hoping to later re-connect) may be forced to remove the cable if chafing is found, which is a more permanent modification. Fourth, the inspection for chafing must follow the service bulletin's limits, but the directive does not reproduce those limits. The operator must obtain APS-07-01-01 from Air Plains Services Corporation or a source that stocks it. Relying on memory or a generic inspection would not satisfy the requirement. Fifth, the replacement fuel line must be part number AE3663161G0190 or an FAA-approved equivalent. Using a different hose, even if functionally identical, would be non-compliant unless it has an FAA approval as an equivalent. Sixth, the directive says later revisions of the service bulletin are acceptable only if approved by the FAA as an AMOC to FAA AD 2007-09-01. An operator who uses a later revision that is not AMOC-approved is non-compliant, even if that revision appears more up-to-date. Seventh, the directive applies only if the aircraft has both the specified STC installed AND a forward ground power receptacle mounted on the firewall. An aircraft with the STC but no forward ground power receptacle appears not to be affected. But if an owner later installs a forward receptacle, the AD would become applicable immediately, triggering the compliance obligations. Eighth, the effective date (27 April 2007) gave operators only about two weeks to comply with the 12 May deadline, which may have required swift sourcing of the service bulletin and any needed parts.

Compliance requires a systematic series of actions, best carried out by a licensed aircraft maintenance engineer (LAME) or a CASR Part 145 approved maintenance organisation. Step one: identify whether the aircraft is affected. Check the model number against the list (182H through 182R). Verify that Air Plains STC SA00152WI is installed by reviewing the aircraft's technical records or the STC identification tag. Check if a ground power receptacle is mounted on the firewall (the "forward ground power receptacle"). If both conditions are met, the AD applies. Step two: obtain a copy of Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01 dated 5 March 2007 (or a later revision that has been approved by the FAA as an AMOC to FAA AD 2007-09-01). This bulletin contains the detailed procedures for disconnection/removal of the cable, repositioning of the fuel strainer cable, the visual inspection, the chafing limits, the replacement hose part number, and the adjustment of the fuel line fitting. Step three: before 12 May 2007, comply with Requirement 1 by either disconnecting the electrical cable at both the forward ground power relay and the starter relay, or removing the cable entirely between those relays. Step four: before further flight after that power removal, fabricate a placard with red letters at least 3mm high on a white background with a red border, reading "Ground Power Receptacle is Inoperative", and install it as close as possible to the forward ground power receptacle. Step five: before 12 May 2007, reposition the fuel strainer cable in accordance with the service bulletin. Step six: before 12 May 2007, visually inspect the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump for chafing. If chafing is found at or beyond the limits defined in the service bulletin, before further flight replace the fuel line with new hose part AE3663161G0190 (or FAA-approved equivalent) and remove the electrical cable per Requirement 1.b (removal, not just disconnection). If chafing is minor and within limits, no replacement is needed but the inspection must be recorded. Step seven: before 12 May 2007, adjust the position of the fuel line fitting at the engine-driven fuel pump per the service bulletin. Step eight: document all actions in the aircraft's maintenance logbook or continuing airworthiness record system, noting the AD number (AD/CESSNA 180/90), the date of compliance, the service bulletin revision used, and any parts replaced (including the part numbers). Keep a copy of the placard installation photo or description. No recurring inspections are stated, but the aircraft's safety case now depends on the removal or disconnection remaining in place. If a later revision of the service bulletin is released without AMOC, the operator may need to check if CASA issues a superseding AD. For ongoing operation, ensure the placard remains legible.