AD 2016-17-05 Airworthiness Directives; RUAG Aerospace Services GmbH Airplanes

Models named: 228-100, 228-101, 228-200, 228-201, 228-202, 228-212. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to RUAG Aerospace Services GmbH Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 airplanes, all serial numbers, certificated in any category.

Unless already done, do the following actions in paragraphs (f)(1) through (4) of this AD based on a compliance time of hours time-in-service (TIS) or flight cycles, whichever occurs first. If the flight cycles or hours TIS of the throttle box assembly is unknown, use the hours TIS of the airplane to determine the compliance time for the inspection. (1) For throttle box assemblies with less than 9,600 hours TIS or 9,600 flight cycles since installed: Inspect the guide pins of the power and condition levers for excessive wear following the Accomplishment Instructions in paragraph 2 of RUAG Aerospace Services GmbH Dornier 228 Alert Service Bulletin No. ASB-228-279, revision 1, dated September 22, 2015, at the following times: (i) Initially, unless already done within the last 1,200 hours TIS or 1,200 flight cycles as of July 24, 2009 (the effective date retained from AD 2009-13-04), before or upon accumulating 9,600 hours TIS or 9,600 flight cycles, or within the next 100 hours TIS or 100 flight cycles after July 24, 2009 (the effective date retained from AD 2009-13-04), whichever occurs later, inspect the guide pins of the power and condition levers for excessive wear; and (ii) Repetitively thereafter within 4,800 hours TIS or 4,800 flight cycles since any previous inspection in which the power and condition levers guide pins were not replaced or within 9,600 hours TIS or 9,600 flight cycles, whichever occurs first, since the previous inspection in which the power and condition levers guide pins were replaced. (2) For throttle box assemblies with 9,600 hours TIS or more or 9,600 flight cycles or more but less than 13,200 hours TIS or 13,200 flight cycles since installed: Inspect the guide pins of the power and condition levers for excessive wear within the next 1,200 hours TIS or 1,200 flight cycles after July 24, 2009 (the effective date retained from AD 2009-13-04) following the Accomplishment Instructions in paragraph 2 of RUAG Aerospace Services GmbH Dornier 228 Alert Service Bulletin No. ASB-228-279, revision 1, dated September 22, 2015; and (i) Repetitively inspect the guide pins of the power and condition levers for excessive wear thereafter within 4,800 hours TIS or 4,800 flight cycles since any previous inspection in which the power and condition levers guide pins were not replaced; or (ii) Repetitively inspect the guide pins of the power and condition levers for excessive wear within 9,600 hours TIS or 9,600 flight cycles since the previous inspection in which the power and condition levers guide pins were replaced. (3) For throttle box assemblies with 13,200 hours TIS or more or 13,200 flight cycles or more since installed: Within 100 hours TIS or 100 flight cycles after July 24, 2009 (the effective date retained from AD 2009-13-04) inspect the guide pins of the power and condition levers for excessive wear following the Accomplishment Instructions in paragraph 2 of RUAG Aerospace Services GmbH Dornier 228 Alert Service Bulletin No. ASB-228-279, revision 1, dated September 22, 2015, at the following times: (i) Initially within the next 100 hours TIS or 100 flight cycles after July 24, 2009 (the effective date retained from AD 2009-13-04); and (ii) Repetitively thereafter within 4,800 hours TIS or 4,800 flight cycles since any previous inspection in which the power and condition levers guide pins were not replaced or within 9,600 hours TIS or 9,600 flight cycles since the previous inspection in which the power and condition levers guide pins were replaced. (4) For all throttle box assemblies: Before further flight after any inspection required in paragraph (f)(1), (2), or (3) of this AD, replace any guide pin that exceeds the acceptable wear-limits as defined in paragraph 4.1 of RUAG Aerospace Services GmbH Dornier 228 Alert Service Bulletin No. ASB-228-279, revision 1, dated September 22, 2015.

The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4123; fax: (816) 329-4090; email: karl.schletzbaum@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as excessive wear on the guide pin of the power lever or condition lever, which could cause functional loss of the flight idle stop. We are issuing this proposed AD to amend the compliance times of the guide pin inspections.

This AD supersedes AD 2009-13-04, Amendment 39-15943 (74 FR 29116; June 19, 2009) (“AD 2009-13-04”).