{"id":"F2007L04020","name":"AD/SWSA226/95 - Pitch Trim Actuator","slug":"ad-swsa226-95-pitch-trim-actuator","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":160810,"registerId":"commonwealth-F2007L04020-current","compilationNumber":null,"startDate":"2026-04-04","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Fairchild (Swearingen) SA226 and SA227 S","sectionType":"division","heading":"Fairchild (Swearingen) SA226 and SA227 Series Aeroplanes","content":"### Fairchild (Swearingen) SA226 and SA227 Series Aeroplanes\n\n| AD/SWSA226/95 | Pitch Trim Actuator | 11/2007 |\n| ------------- | ------------------- | ------- |\n\n```html\n

Applicability:

All Models SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), SA227-PC, and SA227-TT aeroplanes, all serial numbers, that are equipped with pitch trim actuators listed in Table 1 of this AD.

Table 1

Manufacturer

Part Number

Barber-Coleman

27-19008-001
27-19008-002
27-19008-004
27-19008-005
27-19008-006
27-19008-007

Simmonds-Precision

DL5040M5
DL5040M6
DL5040M8

Requirement:

1. For aeroplanes with a pitch trim actuator P/N 27-19008-001, P/N 27-19008-002, P/N 27-19008-004, or P/N 27-19008-005:

Revise the Aircraft Flight Manual (AFM) by incorporating the following restrictions into the Limitations Section.

a. \"Limit the maximum indicated airspeed to manoeuvring airspeed (VA) as shown in the appropriate aircraft flight manual (AFM)''; and

b \"The minimum crew required is two pilots.''

\n```\n\n| | This may be accomplished by inserting a copy of this AD into the AFM.This requirement may be actioned and signed for by a pilot having at least a private pilots licence.Note 1: Fairchild Service Letter 226-SL-017, Fairchild Service Letter 227-SL-033, and Fairchild Service Letter CC7-SL-023, all FAA Approved and dated26 August 1998; Revised 2 September 1998, address the subject matter of this AD.2. For all aeroplanes - Do the following actions at the times specified in the initial inspection or overhaul column and the repetitive inspection or overhaul column in Table 2 of this AD:a. For aeroplanes equipped with a pitch trim actuator P/N DL5040M5,P/N DL5040M6, or P/N DL5040M8 - Measure the freeplay of the pitch trim actuator and inspect the pitch trim actuator for rod slippage using the INSTRUCTIONS section of Fairchild Aircraft SA226 Series Service Letter (SL) 226-SL-005 or Fairchild Aircraft SA227 Series SL 227-SL-011, both Revised: 3 August 1999; or Fairchild Aircraft SA227 Series Service Letter CC7-SL-028, Issued: 12 August 1999, as applicable.b. For aeroplanes equipped with a pitch trim actuator P/N 27-19008-001,P/N 27-19008-002, P/N 27-19008-004, or P/N 27-19008-005 - Do a functional inspection of the pitch trim actuator using the INSTRUCTIONS section of Fairchild Aircraft SA226 Series SL 226-SL-014, Fairchild Aircraft SA227 Series SL 227-SL-031, or Fairchild Aircraft SA227 Series SLCC7-SL-021; all Revised: 1 February 1999; as applicable.c. For aeroplanes equipped with a pitch trim actuator P/N 27-19008-006 orP/N 27-19008-007 - Overhaul the pitch trim actuator following the applicable maintenance manual. |\n| --- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n```html\n


Table 2. - Inspection/Overhaul and Replacement
Requirements for Pitch Trim Actuators

Condition

Initial Inspection or Overhaul

Repetitive
Inspection or Overhaul

Repetitive
Replacement

(i) For all affected aeroplane models (except for the Models SA227-CC and SA227-DC) that have an original
pitch trim actuator, P/N DL5040M5,
installed.

Inspect in accordance with Requirement 2a. of this AD before accumulating
3,000 hours time-in-service (TIS) on the pitch trim actuator or within 50 hours TIS after 17 April 1995, whichever occurs later, unless previously accomplished.

Inspect in accordance with Requirement 2a of this AD before accumulating 250 hours TIS after the initial inspection and repetitively thereafter at intervals not to exceed 250 hours TIS until accumulating the hours TIS specified in paragraph (i) of the Repetitive Replacement column of this Table.

Replace the pitch trim actuator with a P/N DL5040M6, P/N DL5040M8, P/N 27-19008-006, P/N 27-19008-007, or an FAA-approved equivalent pitch trim actuator before accumulating 5,000 hours TIS on the pitch trim actuator, 500 hours TIS after the initial inspection, or within 30 days after effective date of this AD, whichever occurs later.

(ii) For all affected aeroplane models (except for the Models SA227-CC and SA227-DC) that have a replacement
pitch trim actuator, P/N DL5040M5 installed.

Inspect in accordance with Requirement 2a of this AD before accumulating 5,000 hours TIS on the pitch trim actuator or within 50 hours TIS after 17 April 1995 whichever occurs later.

Inspect in accordance with Requirement 2a of this AD before accumulating 300 hours TIS after the initial inspection and repetitively thereafter at intervals not to exceed 300 hours TIS until accumulating the hours TIS specified in paragraph (ii) of the Repetitive Replacement column of this Table.

Replace the pitch trim actuator with a P/N DL5040M6, P/N DL5040M8, P/N 27-19008-006, P/N 27-19008-007, or an FAA-approved equivalent pitch trim actuator before accumulating
6,500 hours TIS on the pitch trim actuator or within 30 days of the effective date of this AD, whichever occurs later.

\n```\n\n```html\n

(iii) For all affected aeroplane models (except for the Models SA227-CC and SA227-DC) that have a replacement
pitch trim actuator, P/N DL5040M6, installed. This part can be new, modified from a P/N DL5040M5 pitch trim actuator, or overhauled and
zero-timed.

Inspect in accordance with Requirement 2a of this AD before accumulating 7,500 hours TIS on the pitch trim actuator or within 50 hours TIS after 17 April 1995, whichever occurs later.

Inspect in accordance with Requirement 2a of this AD before accumulating 300 hours TIS after the initial inspection and repetitively thereafter at intervals not to exceed 300 hours TIS until accumulating the hours TIS specified in paragraph (iii) of the Repetitive Replacement column of this Table.

Replace the pitch trim actuator with a P/N DL5040M6, P/N DL5040M8, P/N 27-19008-006, P/N 27-19008-007, or an FAA-approved equivalent pitch trim actuator before accumulating 9,900 hours TIS on the pitch trim actuator or within 30 days after the effective date of this AD, whichever occurs later.

(iv) For all affected aeroplane models (except for the Models SA227-CC and SA227-DC) that have a replacement pitch trim actuator,
P/N DL5040M5, installed that was overhauled and zero-timed where both nut assemblies, P/N AA56142, were replaced with new assemblies during overhaul.

Inspect in accordance with Requirement 2a of this AD before accumulating 5,000 hours TIS on the pitch trim actuator or within 50 hours TIS after 17 April 1995, whichever occurs later.

Inspect in accordance with Requirement 2a of this AD before accumulating 300 hours TIS after the initial inspection and repetitively thereafter at intervals not to exceed 300 hours TIS until accumulating the hours TIS specified in paragraph (iv) of the Repetitive Replacement column of this Table.

Replace the pitch trim actuator with a P/N DL5040M6, P/N DL5040M8, P/N 27-19008-006, P/N 27-19008-007, or an FAA-approved equivalent pitch trim actuator before accumulating 6,500 hours TIS on the pitch trim actuator or within 30 days after the effective date of this AD, whichever occurs later.

\n```\n\n```html\n

(v) For all affected aeroplane models (except for the Models SA227-CC and SA227-DC) that have a replacement
P/N DL5040M5pitch trim actuator installed that was overhauled and zero-timed where both nut assemblies, P/N AA56142, were not replaced with new assemblies during overhaul.

Inspect in accordance with Requirement 2a of this AD before accumulating 3,000 hours TIS on the pitch trim actuator or within 50 hours TIS after 17 April 1995, whichever occurs later.

Inspect in accordance with Requirement 2a of this AD before accumulating 250 hours TIS after the initial inspection and repetitively thereafter at intervals not to exceed 250 hours TIS until accumulating the hours TIS specified in paragraph (iv) of the Repetitive Replacement column of this Table.

Replace the pitch trim actuator with a P/N DL5040M6, P/N DL5040M8, P/N 27-19008-006, P/N 27-19008-007, or an FAA-approved equivalent pitch trim actuator before accumulating 5,000 hours TIS on the pitch trim actuator or within 30 days after the effective date of this AD whichever occurs later.

(vi) For all affected aeroplane models (except for the Models SA227-CC and SA227-DC) that have a newly fabricated or overhauled and
zero-timed pitch
trim actuator,
P/N 27-19008-001, P/N 27-19008-002, P/N 27-19008-004, or P/N 27-19008-005.

Inspect in accordance with Requirement 2b of this AD before accumulating 500 hours total TIS on the pitch trim actuator or within 50 hours TIS after
1 December 1997, whichever occurs later.

Inspect in accordance with Requirement 2b of this AD before accumulating 300 hours TIS after the initial inspection and repetitively thereafter at intervals not to exceed 300 hours TIS until accumulating the hours TIS specified in paragraph (vi) of the Repetitive Replacement column of this Table.

Replace the pitch trim actuator with a P/N DL5040M6, P/N DL5040M8, P/N 27-19008-006, P/N 27-19008-007, or an FAA-approved equivalent pitch trim actuator before accumulating 5,000 hours TIS on the pitch trim actuator or within 30 days after the effective date of this AD, whichever occurs later.

\n```\n\n```html\n

(vii) For the Models SA227-CC and SA227-DC that have a pitch
trim actuator
P/N DL5040M5 or P/N DL5040M6 installed.

None.

None.

Replace the pitch trim actuator with a P/N DL5040M8,
P/N 27-19008-006 P/N 27-19008-007, or an FAA-approved equivalent pitch trim actuator before accumulating 1,500 hours TIS on the pitch trim actuator or within 30 days after the effective date of this AD, whichever occurs later.

(viii) For the Models SA227-CC and SA227-DC that have a newly fabricated or overhauled and zero-timed pitch trim actuator,
P/N 27-19008-001, P/N 27-19008-002, P/N 27-19008-004, or P/N 27-19008-005.

Inspect in accordance with Requirement 2b of this AD before accumulating 500 hours total TIS on the pitch trim actuator or within 50 hours TIS after 1 December 1997, whichever occurs later.

Inspect in accordance with Requirement 2b of this AD before accumulating 300 hours TIS after the initial inspection and repetitively thereafter at intervals not to exceed 300 hours TIS until accumulating the hours TIS specified in paragraph (viii) of the Repetitive Replacement column of this Table.

Replace the pitch trim actuator with a P/N DL5040M8,
P/N 27-19008-006, P/N 27-19008-007, or an FAA-approved equivalent pitch trim actuator before accumulating 5,000 hours TIS on the pitch trim actuator or within 30 days after the effective date of this AD, whichever occurs later.

\n```\n\n```html\n

(ix) For all affected aeroplanes with a pitch trim actuator, P/N DL5040M8, installed.

Inspect in accordance with Requirement 2a of this AD before accumulating 7,500 hours TIS on the pitch trim actuator or within the next 50 hours TIS after
April 10, 2000, whichever occurs later.

Inspect in accordance with Requirement 2a of this AD before accumulating 300 hours TIS after the initial inspection and repetitively thereafter at intervals not to exceed 300 hours TIS until accumulating the hours TIS specified in paragraph (ix) of the Repetitive Replacement column of this Table.

Replace the pitch trim actuator with a P/N DL5040M8,
P/N 27-19008-006 or P/N 27-19008-007, or an FAA-approved equivalent pitch trim actuator before accumulating 9,900 hours TIS on the pitch trim actuator or within 30 days after the effective date of this AD, whichever occurs later.

(x) For all affected aeroplanes with a P/N 27-19008-006 or 27-19008-007 pitch trim actuator installed.

Overhaul following Requirement 2c of this AD before accumulating 2,000 hours TIS on the pitch trim actuator.

Overhaul following Requirement 2c of this AD before accumulating 2,000 hours TIS on the pitch trim actuator.

No replacement requirements.

3. For all aeroplanes - Replace the pitch trim actuator following the applicable maintenance manual.

4. For all aeroplane models except Models SA227-CC and SA227-DC - Do not install as a replacement any of the following pitch trim actuators or FAA-approved equivalent P/Ns:

a. P/N 27-19008-001;

b. P/N 27-19008-002;

c. P/N 27-19008-004;

d. P/N 27-19008-005; or

e. P/N DL5040M5.

\n```\n\n| | 5. For all aeroplane Models SA227-CC and SA227-DC - Do not install as a replacement any of the following pitch trim actuators or FAA- approved equivalent P/Ns:a. P/N 27-19008-001;b. P/N 27-19008-002;c. P/N 27-19008-004;d. P/N 27-19008-005;e. P/N DL5040M5; orf. P/N DL5040M6.Note 2: FAA AD 2007-16-03 Amdt 39-15142 dated 27 July 2007 refers. This AD supersedes FAA AD 98-19-15R and AD 2000-03-17. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Compliance: | 1. Remains unchanged as detailed in AD/SWSA 226/85 Amdt 1 as - Before further flight after 14 September 1998; or in the case of aircraft with actuators P/N27-19008-004, or P/N 27-19008-005, before further flight after 23 February 2000.Installation of any FAA-approved pitch trim actuator other than P/N27-19008-001, P/N 27-19008-002, P/ N 27-19008-004, or P/N 27-19008-005 terminates the actions detailed in Requirement 1 of this AD.2. As detailed in Table 2 of this AD.3. Before further flight when any of the following occurs:a. The pitch trim actuator is inspected following Requirement 2 of this AD and the freeplay limitations are exceeded, rod slippage is found, or a ratcheting sound occurs, as specified in the applicable service letters; orb. The installed pitch trim actuator reaches its repetitive replacement time as specified in table 2 of this AD.4. From the effective date of this AD.5. From the effective date of this AD. |\n| | This Airworthiness Directive becomes effective on 25 October 2007. |\n\n| Background: | This AD results from reports of mechanical failure of the pitch trim actuator causing the horizontal stabilizer to move to full aircraft nose up. The issuing of this AD is intended to detect excessive freeplay or rod slippage in the pitch trim actuator, which, if not detected and corrected, could result in pitch trim actuator failure. It is also intended to lessen the severity of pitch upset if a pitch trim actuator mechanical failure occurs. These conditions could lead to possible loss of control. The issuing of this AD will also eliminate the use of certain pitch trim actuators that require frequent critical inspections or replacements.This AD supersedes AD/SWSA226/68 Amdt 5 and AD/SWSA226/85 Amdt 1 which are cancelled. |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png) \nCharles Lenarcic \nDelegate of the Civil Aviation Safety Authority\n\n10 September 2007","sortOrder":0},{"sectionNumber":"AD/SWSA226/95","sectionType":"part","heading":"AD/SWSA226/95","content":"## AD/SWSA226/95","sortOrder":1},{"sectionNumber":"Pitch Trim Actuator","sectionType":"part","heading":"Pitch Trim Actuator","content":"## Pitch Trim Actuator","sortOrder":2},{"sectionNumber":"11/2007","sectionType":"part","heading":"11/2007","content":"## 11/2007","sortOrder":3}],"analysis":{"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"},"kimi_summary":{"content_quality":"ok","complexity_score":7,"scope_assessment":{"changed":true,"description":"This AD has evolved significantly from its original scope. It began as a response to specific pitch trim actuator failures but has expanded through multiple amendments to cover: additional actuator part numbers (27-19008-004, 27-19008-005, 27-19008-006, 27-19008-007, DL5040M8), different aircraft models (adding SA227-CC and SA227-DC with distinct requirements), varying overhaul histories, and different compliance timelines based on whether actuators are original equipment or replacements. The directive now manages a complex lifecycle of ten different condition categories with distinct inspection, replacement, and overhaul schedules, rather than a simple one-size-fits-all safety fix."},"complexity_factors":["Multiple nested tables (Table 1 and Table 2) with 10 distinct condition categories (i-x) each with different inspection intervals, replacement thresholds, and compliance dates","Extensive cross-referencing to manufacturer service letters (226-SL-005, 227-SL-011, CC7-SL-028, etc.) and FAA ADs (2007-16-03, 98-19-15R, 2000-03-17)","Complex conditional logic based on: aircraft model, actuator part number, whether actuator is original or replacement, overhaul history, whether nut assemblies were replaced during overhaul, and accumulated flight hours (Time-In-Service)","Multiple effective dates and compliance deadlines referenced (17 April 1995, 1 December 1997, 14 September 1998, 23 February 2000, 10 April 2000, 25 October 2007)","Supersedes and cancels previous ADs (AD/SWSA226/68 Amdt 5 and AD/SWSA226/85 Amdt 1) with partial incorporation of their requirements","Different requirements for SA227-CC and SA227-DC models versus all other affected models","Specific technical measurements required (freeplay limitations, rod slippage detection, ratcheting sounds)"],"plain_english_summary":"This CASA Airworthiness Directive mandates inspections, replacements, overhauls, flight manual limits, crew requirements, and bans on certain replacement parts for Barber‑Coleman and Simmonds‑Precision pitch trim actuators installed on specified Fairchild (Swearingen) SA226/SA227 aircraft. \n\nIt responds to actuator failures that drove the horizontal stabilizer to full nose‑up, creating a high risk of loss of control, so operators must take the listed actions to detect and mitigate that hazard."},"flash_summary":{"complexity_score":7,"scope_assessment":{"changed":true,"description":"Yes. The AD supersedes earlier CASA and FAA ADs (Background; Note 2) and expands mandatory actions: it adds AFM limitations, prescribes part‑number specific inspection/overhaul methods and detailed time‑in‑service replacement schedules, and bans certain actuator P/Ns as replacements for most models while retaining limited exceptions for SA227‑CC/DC (Requirement 1; Table 2; paras 3–5). This shifts ongoing compliance and replacement costs onto operators and tightens permitted parts installation."},"complexity_factors":["Multiple affected airframe models and many specific actuator part numbers to track (Applicability; Table 1).","Model‑specific initial and repetitive inspection intervals and different replacement thresholds in Table 2 (Table 2: paragraphs (i)–(x)).","Different inspection methods required depending on part number (measure freeplay/rod slippage vs functional inspection vs overhaul) (Requirement 2a–2c).","Staggered compliance triggers (hours TIS, calendar deadlines, or next flight after specified dates) increase scheduling complexity (Table 2; Compliance).","Installation prohibitions on particular P/Ns for most models and additional prohibitions for SA227‑CC/DC require parts control and supply management (paras 4–5).","References to multiple manufacturer service letters and FAA ADs as the source of inspection instructions create cross‑document dependencies (Note 1; Note 2; Requirement 2).","AFM amendment requirement (Limitations: V_A speed cap and two‑pilot minimum) that may be signed by a privately‑licensed pilot (Requirement 1; Note 1) introduces an administrative compliance step.","Supersession of earlier ADs and alignment with FAA directives alters historical compliance baselines (Background; Note 2)."],"plain_english_summary":"This directive requires operators of Fairchild SA226/SA227 aeroplanes fitted with the listed pitch‑trim actuators to revise the AFM (speed and crew limits), carry out specified inspections or overhauls, and replace or prohibit certain actuator part numbers on set time‑in‑service schedules. CASA states the AD is intended to detect freeplay/rod slippage and reduce pitch‑up risk; the measures place inspection, overhaul and replacement costs and recurring maintenance obligations on aircraft owners/operators and restrict permissible replacement parts (Applicability; Requirement 1; Table 2)."}},"importantCases":[],"_links":{"self":"/api/acts/ad-swsa226-95-pitch-trim-actuator","history":"/api/acts/ad-swsa226-95-pitch-trim-actuator/history","analysis":"/api/acts/ad-swsa226-95-pitch-trim-actuator/analysis","conflicts":"/api/acts/ad-swsa226-95-pitch-trim-actuator/conflicts","importantCases":"/api/acts/ad-swsa226-95-pitch-trim-actuator/important-cases","documents":"/api/acts/ad-swsa226-95-pitch-trim-actuator/documents"}}