{"id":"F2007L01729","name":"AD/ATR 42/1 - State of Design Airworthiness Directives","slug":"ad-atr-42-1-state-of-design-airworthiness-directives","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":66447,"registerId":"commonwealth-F2007L01729-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Avions de Transport Regional ATR 42 Seri","sectionType":"division","heading":"Avions de Transport Regional ATR 42 Series Aeroplanes","content":"### Avions de Transport Regional ATR 42 Series Aeroplanes\n\n| AD/ATR 42/1 | State of Design Airworthiness Directives | 8/2007 DM |\n| ----------- | ---------------------------------------- | --------- |\n\n```html\n

Applicability:

ATR 42 series aeroplanes, as identified in the individual Airworthiness Directive (AD) listed Tables 1 and 2.

Requirement:

1. Determine the applicability of the ADs issued by the Direction Générale de l’Aviation Civile of France (DGAC), listed in Table 1, and the ADs issued by the European Aviation Safety Agency (EASA), listed in Table 2.

2. If it is determined that an DGAC or EASA AD listed in Table 1 or 2 is applicable and has not been previously accomplished, perform the actions required by that AD.

Table 1

DGAC AD

Issue Date

Title

F-1986-085-002 R1

28 May 1986

Oil cooling system

F-1986-078-001 R1

23 July 1986

Ipeco pilot and copilot seats - ATR Airplanes

F-1986-130-003 R1

26 March 1997

Flaps 45º Configuration

F-1987-022-004

4 January 1987

Automatic stop of the flight and cockpit voice recorders

F-1987-046-005 R1

10 June 1987

Attitude and heading system

F-1987-155-007

10 November 1987

Elevator trims

F-1987-156-008 R1

16 November 1988

Propeller brake control system

F-1987-173-009

9 December 1987

Protection for auto pilot roll actuator

F-1988-051-010 R2

21 February 1990

Fuel quantity indicators

F-1988-070-011

11 May 1988

Rudder control channel cables

F-1988-080-012

22 June 1988

Engine and propeller flexible control shafts

F-1988-092-013

17 August 1988

Honeywell-Sperry navigation equipment

\n```\n\n| | F-1988-135-014 | 19 October 1988 | Main gear wheel bearing |\n| --- | ----------------- | ---------------- | ------------------------------------------------------------------------- |\n| | F-1988-147-015 | 16 November 1988 | Propeller brake control pushbutton |\n| | F-1988-186-016 R1 | 31 May 1989 | Test system of the smoke detectors in cargo compartment areas |\n| | F-1989-033-019 R1 | 31 May 1989 | Pitch trim |\n| | F-1989-042-018 R1 | 5 April 1989 | Oil pressure transmitter manifold |\n| | F-1989-067-020 R2 | 20 March 1991 | Main L/G retraction jacks fitting bolts |\n| | F-1989-077-021 R2 | 19 July 1989 | Aileron tab inboard hingepin |\n| | F-1989-093-022 | 28 June 1989 | Automatic cut-off of the voice recorders |\n| | F-1989-197-025 R1 | 4 April 1990 | Fire extinguishing system |\n| | F-1990-028-026 | 21 February 1990 | Nose landing gear retraction system |\n| | F-1990-029-027 | 21 February 1990 | Emergency lighting |\n| | F-1990-030-028 R1 | 23 January 1991 | Propeller brake |\n| | F-1990-109-029 | 13 June 1990 | Main frames |\n| | F-1990-155-030 R1 | 27 November 1991 | Emergency oxygen system for cabin attendants |\n| | F-1990-163-031 | 3 October 1990 | Structure modification resulting from fatigue tests landing gear bay area |\n| | F-1990-193-032 R2 | 8 July 1992 | Hydraulic system - Low pressure warning |\n| | F-1990-201-033 R2 | 23 April 1997 | Flight controls |\n| | F-1991-005-036 | 9 January 1991 | Nose landing gear |\n| | F-1991-068-039 | 20 march 1991 | Flight controls |\n| | F-1991-081-040 R1 | 6 June 1991 | Main landing gear |\n| | F-1991-157-041 | 31 July 1991 | Nose landing gear |\n| | F-1991-214-042 | 2 October 1991 | Flight controls |\n| | F-1991-216-043 R1 | 22 January 1992 | Engine and propeller flexible controls |\n\n| | F-1991-237-044 | 30 October 1991 | Auto pilot |\n| --- | ----------------- | ----------------- | -------------------------------------------------------- |\n| | F-1992-043-045 | 19 February 1992 | Commercial furnishing |\n| | F-1992-122-047 | 27 May 1992 | ECE push-button |\n| | F-1992-133-048 R1 | 19 August 1992 | Pitch control |\n| | F-1992-197-049 | 30 September 1992 | Autopilot |\n| | F-1993-205-052 | 8 December 1993 | Pitch trim controls |\n| | F-1994-003-053 | 5 January 1994 | Flight control rods |\n| | F-1994-004-054 | 5 January 1994 | Roll trim |\n| | F-1994-005-055 | 5 January 1994 | Nose Landing Gear Nardi hinge pins |\n| | F-1994-162-056 | 6 July 1994 | Karman fairing attachment clips |\n| | F-1995-051-058 | 15 March 1995 | Main landing gear side brace pin |\n| | F-1995-103-059 | 24 May 1995 | Protection of the electrical harness in front area |\n| | F-1995-127-062 | 21 June 1995 | Corrosion on wing rear spar (ATA 57) |\n| | F-1996-109-063 | 5 June 1996 | Engine nacelle drain system |\n| | F-1996-131-064 | 3 July 1996 | Main landing Gear - Pins Magnaghi |\n| | F-1996-132-065 | 3 July 1996 | Fuselage - Stringer 6 to frame 34 junction |\n| | F-1996-208-067 R1 | 21 April 1999 | De-icing procedures and protection improvements (ATA 30) |\n| | F-1996-230-066 | 23 October 1996 | Standby horizon - Power supply |\n| | F-1996-256-068 | 6 November 1996 | Stick shaker/pusher system |\n| | F-1996-289-069 R1 | 18 December 1996 | Forward cargo compartment nets |\n| | F-1997-115-070 R1 | 11 February 1998 | Fuselage - Main landing gear actuator fitting |\n| | F-1997-159-071 | 16 July 1997 | Karman fairing panel fasteners |\n| | F-1997-328-072 R1 | 19 November 1997 | Flight controls - Rudder |\n\n| | F-1998-069-073 | 11 February 1998 | Engine mount and upper engine fairing stiffener fouling |\n| --- | ----------------- | ----------------- | ------------------------------------------------------------------------------------- |\n| | F-1998-070-074 | 11 February 1998 | Rotron recirculation fan |\n| | F-1999-014-076 R2 | 10 December 2003 | Icing conditions - Revise the Airplane Flight Manual (AFM) |\n| | F-1999-165-077 R1 | 12 July 2000 | Severe icing conditions - Implement aircraft design enhancements (ATA 30) |\n| | F-2000-189-078 | 3 May 2000 | Landing Gears - Install modified uplock boxes (ATA 32) |\n| | F-2000-281-078 R1 | 19 September 2001 | Fire protection - Fire handles (ATA 26) |\n| | F-2000-449-082 R2 | 19 September 2001 | Take-off after use of type II or IV fluids - Appendix to the Flight Manual (ATA 04) |\n| | F-2000-454-081 | 15 November 2000 | Electrical system - Engine start selector (ATA 24, 80) |\n| | F-2001-214-084 | 30 May 2001 | Propeller feathering -ATPCS test selector switch (ATA 24, 61) |\n| | F-2001-387-085 | 5 September 2001 | Flight controls - Normal pitch trim switches |\n| | F-2001-554-087 R1 | 2 October 2002 | Wing to fuselage fairing panel (ATA 53) |\n| | F-2002-071-091 | 23 January 2002 | Engines - High pressure oil pump - Pressure Regulating Valve (PRV) (ATA 79) |\n| | F-2002-090-092 | 20 February 2002 | Electrical rack 90VU - Wire bundle routing on 93, 94 and 95VU carbon shelves (ATA 92) |\n| | F-2002-431 | 21 August 2002 | Flight controls - Pitch control interface |\n| | F-2002-539 | 30 October 2002 | Forward attendant seat (ATA 25) |\n| | F-2003-106 R1 | 16 April 2003 | Flight controls - Stand by pitch trim switch (ATA 92) |\n| | F-2003-376 | 1 October 2003 | Main Landing Gear - Swinging lever (ATA 32) |\n| | F-2004-191 | 22 December 2004 | Wings - Outer wing boxes - Upper skin and ribs |\n| | F-2005-160 | 12 October 2005 | Fuel - Fuel quantity indicators |\n\n```html\n

Table 2

EASA AD

Issue Date

Title

2006-0216-E

14 July 2006

Main Landing Gear - Shock absorber - Cross locking bolt of the attachment pin

2006-0283

14 September 2006

Electrical Power - 120 VU Electrical Harness - Inspection

Note: EASA and DGAC ADs may be accessed via the internet at the following URLs:

http://ad.easa.europa.eu/

http://www.gsac.fr/php/P_ConsignesNav.php

Compliance:

For Requirements 1 and 2 - Within 30 days after the effective date of this Directive or prior to the issue of a Certificate of Airworthiness, whichever occurs first.

This Airworthiness Directive becomes effective on 22 June 2007.

Background:

The DGAC and EASA ADs listed in Table 1 and 2 of this Directive require one time actions for which the compliance date and/or period has passed. CASA has determined that these ADs may be applicable to recently registered or imported Australian aircraft. This Directive is issued to ensure all State of Design ADs are complied with.

CASA appreciates that, due to date of aircraft manufacture or aircraft configuration and modification status, not all the ADs listed in Table 1 and 2 will be applicable to all ATR 42 series aeroplanes.

\n```\n\n![](image.001.png) \nDavid Punshon \nDelegate of the Civil Aviation Safety Authority\n\n8 June 2007","sortOrder":0},{"sectionNumber":"AD/ATR 42/1","sectionType":"part","heading":"AD/ATR 42/1","content":"## AD/ATR 42/1","sortOrder":1},{"sectionNumber":"State of Design Airworthiness Directives","sectionType":"part","heading":"State of Design Airworthiness Directives","content":"## State of Design Airworthiness Directives","sortOrder":2},{"sectionNumber":"8/2007 DM","sectionType":"part","heading":"8/2007 DM","content":"## 8/2007 DM","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This AD appears to serve its original purpose as a 'catch-all' mechanism to ensure recently imported or registered ATR 42 aircraft comply with historical State of Design airworthiness directives. The scope is appropriately limited to adopting specific pre-existing foreign ADs rather than expanding into new regulatory territory."},"complexity_factors":["Extensive cross-referencing to external documents: 50+ individual DGAC and EASA directives listed across two tables","Conditional applicability: Operators must self-assess which of the 50+ foreign ADs apply based on aircraft-specific factors (manufacture date, configuration, modification status)","Dual regulatory framework: Incorporates directives from two different foreign authorities (French DGAC and European EASA) with different numbering systems","Temporal complexity: Many referenced ADs have compliance dates that already passed in their home jurisdictions, requiring retrospective assessment","Technical density: Covers highly specialised aircraft systems (ATA chapters 24, 25, 26, 30, 32, 53, 57, 61, 79, 80, 92) requiring engineering expertise to interpret"],"plain_english_summary":"CASA’s AD requires Australian-registered ATR 42 operators and maintenance organisations to adopt specific DGAC/EASA safety directives. Operators must determine whether the listed foreign directives apply to their aircraft and, if so, complete any outstanding mandatory corrective actions; these measures address critical systems (flight controls, landing gear, engines, fire/icing/electrical protection) and must be complied with within 30 days or before issuing an Australian Certificate of Airworthiness."},"flash_summary":{"complexity_score":5,"scope_assessment":{"changed":false,"description":"This directive does not materially broaden the original regulatory purpose. Its stated intent is to ensure Australian‑registered ATR 42 aeroplanes comply with State‑of‑Design (DGAC/EASA) one‑time ADs whose compliance dates have passed. Mechanically it consolidates and domesticates those foreign ADs for Australian operators (by listing them and making them mandatory where applicable) but does not add new technical mandates beyond the ADs themselves. The instrument therefore aligns domestic obligations with the original safety requirements from the State of Design rather than expanding the scope of regulatory intervention."},"complexity_factors":["Cross‑reference to a large list of foreign ADs (Table 1 lists dozens of DGAC ADs covering 1986–2005; Table 2 lists EASA ADs)","Obligation is conditional (operator must first determine applicability for each aircraft and only then perform actions if not previously accomplished)","Compliance timing constraint: 30 days after effective date or before issue of Certificate of Airworthiness (whichever first)","Dependence on external documents hosted off‑site (EASA and DGAC web databases) for the detailed technical requirements","Variations in applicability by aircraft configuration, modification status and manufacture date (creates per‑aircraft factual enquiries)","One‑time actions with past compliance dates (creates retrospective compliance complexity)","Operational and logistical dependencies (availability of parts, approved modification kits, certified maintenance providers)","Enforcement and certification mechanics require interaction between operators, certified maintenance organisations and CASA delegates"],"plain_english_summary":"**What this instrument does (mechanically)**\n\n- It requires operators/owners of ATR 42 series aeroplanes on the Australian register to check whether a specified list of foreign airworthiness directives (ADs) issued by the French design authority (DGAC) and by EASA apply to each aircraft (Requirement 1, Table 1 and Table 2).\n- If any listed DGAC or EASA AD is applicable to an individual aeroplane and that AD has not already been complied with, the operator must carry out the actions required by that AD (Requirement 2).\n- The required checks and any corrective actions must be completed within 30 days of the directive coming into effect or before a Certificate of Airworthiness is issued (whichever happens first).\n\n**Who is affected**\n\n- Owners and operators of ATR 42 series aeroplanes registered in Australia. That includes aircraft recently imported or newly registered where the original AD compliance dates (set by the State of Design) may have already passed.\n- Maintenance organisations, approved engineers and parts suppliers who will perform and certify any required inspections, repairs or modifications.\n\n**Why it matters**\n\n- The directive brings Australian-registered ATR 42 aeroplanes into alignment with a long list of State-of-Design (DGAC/EASA) mandatory one‑time ADs that may already have required actions. In practical terms, it closes a compliance gap for aircraft that changed registration or for which the original compliance deadlines have passed.\n\n**Official purpose claim and practical implications**\n\n- The Civil Aviation Safety Authority (CASA) states the directive is issued because a number of one‑time DGAC/EASA ADs have compliance dates that have already passed, and recently registered/imported Australian aircraft might still need those actions completed (Background). That is the declared purpose.\n\n- The practical effects of that purpose are: (a) operators must examine historical modification and maintenance records for each listed AD; (b) operators will have to arrange any outstanding inspections/modifications; and (c) the work must be done within a short statutory window (30 days or before a CoA is issued).\n\n**Costs, incentives, trade‑offs and who pays**\n\n- Direct costs fall on aircraft owners/operators: administrative time to determine applicability, costs of inspections, parts and labour to carry out AD requirements, and potential downtime while work is done.\n- Maintenance organisations and parts suppliers will receive business from the required works; if specific parts are scarce or replacements require design approvals, that can increase cost and delay completion.\n- There is a compliance‑time trade‑off: the 30‑day window pushes operators to prioritise these checks, which may displace other maintenance work or require temporary schedule changes.\n\n**Bureaucratic discretion, implementation risk and compliance burden**\n\n- CASA has exercised discretion by consolidating State-of-Design ADs into a domestic directive and by setting the compliance window; however, the technical content of required actions is imported from the DGAC/EASA ADs themselves (Tables 1 and 2).\n- Implementation risks include incomplete historic records on imported aircraft, uncertainty about whether a particular AD truly applies to a specific aircraft configuration, lead time for parts or approved modification kits, and workload on certified maintenance providers.\n\n**Effects on private enterprise and competition**\n\n- The directive increases demand for approved maintenance and engineering services for ATR 42 aircraft. That is likely to benefit certified MROs and parts vendors with the right approvals and inventories.\n- Smaller operators or independent owners may face tighter cashflow or scheduling pressure because they must fund and arrange the works within the deadline.\n\n**Conditions and special notes**\n\n- CASA recognises not every AD listed will apply to every ATR 42 because of differences in manufacture date, configuration or previous modifications (Background).\n- The directive points operators to the EASA and DGAC AD databases (URLs included in the directive) for the full text of each foreign AD; CASA’s directive does not reproduce the full technical requirements but makes compliance with those foreign ADs mandatory where applicable.\n\n(Referenced parts of the instrument: Requirements 1 and 2; Tables 1 and 2 listing DGAC and EASA ADs; Compliance timing; Background.)"},"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"}},"importantCases":[],"_links":{"self":"/api/acts/ad-atr-42-1-state-of-design-airworthiness-directives","history":"/api/acts/ad-atr-42-1-state-of-design-airworthiness-directives/history","analysis":"/api/acts/ad-atr-42-1-state-of-design-airworthiness-directives/analysis","conflicts":"/api/acts/ad-atr-42-1-state-of-design-airworthiness-directives/conflicts","importantCases":"/api/acts/ad-atr-42-1-state-of-design-airworthiness-directives/important-cases","documents":"/api/acts/ad-atr-42-1-state-of-design-airworthiness-directives/documents"}}