Airworthiness Directive · Amendment 39-11576 · Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes
Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes
Superseded. A later AD replaced this one: AD 2007-16-03. Comply with the one in force.
All SA226 and SA227 series airplanes (all models and serial numbers), certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment supersedes Airworthiness Directive (AD) 97-23- 01, which currently requires the following on Fairchild Aircraft, Inc. (Fairchild Aircraft) SA226 and SA227 series airplanes that are equipped with a certain Simmonds-Precision pitch trim actuator or a certain Barber-Colman pitch trim actuator: repetitively measuring the freeplay of the pitch trim actuator and repetitively inspecting the actuator for rod slippage; immediately replacing any actuator if certain freeplay limitations are exceeded or rod slippage is evident; and eventually replacing the actuator regardless of the inspection results. This AD retains the actions of AD 97-23-01, and adds these requirements on airplanes with different design pitch trim actuators installed. This AD is the result of the manufacturer developing different design pitch trim actuators and the Federal Aviation Administration (FAA) determining that these actuators should be subject to the actions of AD 97-23-01. The actions specified by this AD are 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 and possible loss of control of the airplane.
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 and possible loss of control of the airplane, accomplish the following:
Note 2: The paragraph structure of this AD is as follows:
Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.
Level 2 and Level 3 structures are designations of the Level 1 paragraph they immediately follow.
(a) Accomplish the following at the times specified in the chart in paragraph (b) of this AD:
(1) Initial and repetitive inspections:
(i) For airplanes equipped with a Simmonds-Precision actuator, P/N DL5040M5, P/N DL5040M6, or P/N DL5040M8, measure the freeplay (inspection) of the pitch trim actuator and inspect the actuator for rod slippage in accordance with 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: August 3, 1999; or Fairchild Aircraft SA227 Series Service Letter CC7-SL-028, Issued: August 12, 1999, as applicable.
(ii) For airplanes equipped with Barber-Colman actuators, P/N 27-19008-00-001, P/N 27-19008-002, P/N 27-19008-00-004, or P/N 27-19008-005, conduct a functional inspection of the actuator in accordance with the INSTRUCTIONS section of Fairchild Aircraft SA226 Series SL 226-SL-014, Revised: February 1, 1999, Fairchild Aircraft SA227 Series SL 227-SL-031, Revised: February 1, 1999, or Fairchild Aircraft SA227 Series SL CC7-SL-021, Revised: February 1, 1999, whichever is applicable.
Note 3: The actions in this AD are the same as the actions in AD 97-23-01, except for the actions added to the airplanes equipped with improved design pitch trim actuators.
(2) Initial and repetitive replacements: Replace the pitch trim actuator with any of the pitch trim actuators presented in the Chart in paragraph (b) of this AD, as applicable, at the time specified in the Repetitive Replacement column of this chart. However, if certain freeplay limitations that are specified in the service letters are exceeded or if rod slippage is found, prior to further flight, replace the pitch trim actuator.
(b) The following chart presents the pitch trim actuator that could be installed and the initial and repetitive inspection and replacement compliance times of this AD:
| Condition | Initial inspection | Repetitive inspection | Repetitive replacement |
|---|---|---|---|
| For all affected airplane models, except for the Models SA227-CC and SA227-DC, with an original Simmonds-Precision actuator, P/N DL5040M5, installed | Upon accumulating 3,000 hours TIS on a Simmonds-Precision P/N DL5040M5 actuator or within 50 hours TIS after April 17, 1995 (the effective date of AD 93-15-02 R1), whichever occurs later | Every 250 hours TIS after the initial inspection until accumulating 5,000 hours TIS on the actuator or 500 hours TIS after the last inspection required by AD93-15-02 R1. whichever occurs later | Initially upon accummulating 5,000 hours TIS on the actuator or 500 hours TIS after the initial inspection, whichever occurs later, and thereafter as indicated below. |
| For all affected airplane models, except for the Models SA227-CC and SA227-DC, with a replacement Simmonds-Precision actuator, PN/DL5040M5, installed | Initially upon accummulating 5,000 hours TIS on the new actuator or within 50 hours TIS after April 17, 1995 (the effective date of AD 93-15-02 R1), whichever occurs later | Every 300 hours TIS after the initial inspection until accumulating 6,500 hours TIS on the actuator | Upon accumulating 6,500 hours TIS on the actuator. |
| For all affected airplane models, except for the Models SA227-CC and SA227-DC, with a replacement Simmonds-Precision actuator, P/N DL5040M6, installed. This part can be new, modified from a P/N DL5040M5 actuator, or overhauled and zero-timed | Initially upon accumulating 7,500 hours TIS on the new or modified actuator or within 50 hours TIS after April 17, 1995 (the effective date of AD 93-15-02 R1), whichever occurs later | Every 300 hours TIS after the initial inspection until accumulating 9,900 hours TIS on the actuator | Upon accumulating 9,900 hours TIS on the actuator. |
| For all affected airplanes models, except for the Models SA227-CC and SA227-DC, with a replacement Simmonds-Precision 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 | Initially upon accumulating 5,000 hours TIS on the overhauled actuator or within 50 hours TIS after April 17, 1995 (the effective date of AD 93-15-02 R1), whichever occurs later | Every 300 hours TIS after the initial inspection until accumulating 6,500 hours TIS on the actuator | Upon accumulating 6,500 hours TIS on the actuator. |
| For all affected airplanes models, except for the Models SA227-CC and SA227-DC, with a replacement P/N DL5040M5 actuator installed that was overhauled and zero-timed where both nut assemblies, P/N AA56142, were not replaced with new assemblies during overhaul | Initially upon accumulating 3,000 hours TIS on the overhauled actuator or within 50 hours TIS after April 17, 1995 (the effective date of AD 93-15-02 R1), whichever occurs later | Every 250 hours TIS after the initial inspection until accumulating 5,000 hours TIS on the actuator | Upon accumulating 5,000 hours TIS on the actuator. |
| For all affected airplanes models with a newly fabricated or overhauled and zero-timed Barber-Colman actuator, P/N 27-19008-001-004 or P/N 27-19008-002-005 | Upon accumulating 500 hours total TIS on the newly fabricated or overhauled and zero-timed actuator or within 50 hours TIS after the effective date of AD 97-23-01, whichever occurs later | Every 300 hours TIS after the initial inspection | None. |
| For the Models SA227-CC and SA227-DC only, with a Simmonds-Precision pitch trim actuator, P/N DL5040M5 or P/NDL5040M6, installed | None | None | Upon accumulating 1,500 hours TIS on the actuator. |
| For all affected airplanes with a Barber-Colman P/N 27-19008-006 or 27-19008-007 actuator installed | Must be overhauled upon the accumulation of 2,000 hours TIS on the actuator | Must be overhauled at intervals not to exceed 2,000 hours EIS | No replacement requirements. |
| For all affected airplanes with a Simmonds-Precision pitch trim actuator, PN DL5040M8, installed | Upon accumulating 7,500 hours TIS on the actuator of within the next 50 hours TIS after the effective date of this AD, whichever occurs later | Every 600 hours TIS after the initial inspection until accumulating, 9,900 hours TIS | Upon accumulating 9,900 hours TIS on the actuator. |
