Results
2012-23-09: We are superseding an existing airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. That AD currently requires revising the maintenance program to incorporate modifications in the Airworthiness Limitation Section (ALS) of the EMBRAER ERJ 190 Maintenance Review Board Report (MRBR). This new AD requires revising the maintenance program to incorporate modifications in the ALS of the EMBRAER ERJ 190 MRBR to include new inspection tasks and their respective thresholds and intervals. This AD was prompted by issuance of new inspection tasks and their respective thresholds and intervals. We are issuing this AD since failure to inspect these structural components according to the new ALS tasks, thresholds, and intervals could prevent a timely detection of fatigue cracking, which if not properly addressed, could result in reduced structural integrity of the airplane.
2012-23-07: We are adopting a new airworthiness directive (AD) for all Eurocopter Deutschland GmbH (ECD) Model EC135 helicopters, except the EC 135 P2+ and T2+. This AD requires inspecting each upper and lower plain journal bearing (bearing) and replacing the swashplate assembly with an airworthy swashplate assembly if a bearing is not correctly positioned. This AD was prompted by two reports of the bearings moving in relation to the main rotor swashplate sliding sleeve (sliding sleeve). The actions of this AD are intended to detect shifting of the bearing, which could limit the movement of the collective control and result in subsequent loss of control of the helicopter.
90-08-04: 90-08-04 BRITISH AEROSPACE: Amendment 39-6560. Docket No. 89-NM-259-AD. Applicability: Certain Model BAC 1-11 200 and 400 series airplanes, as listed in British Aerospace Service Bulletin 52-A-PM3682, Issue 1, dated August 30, 1968, certificated in any category. Compliance: Required within 90 days after the effective date of this AD, unless previously accomplished. To prevent fatigue damage to the service door and subsequent decompression of the airplane, accomplish the following: A. Check the serial number plate located on the rear edge of the service door to determine if the service door part number and serial number correspond to the part number and serial number identified on page 1 of British Aerospace Service Bulletin 52-A-PM3682, Issue 1, dated August 30, 1968, 1. If the service door part number and serial number do not correspond with those in the service bulletin, no further action is required. 2. If the service door part number and serial number correspond with those in the service bulletin, perform an inspection using a micrometer or other suitably accurate instrument, taking three measurements on the lip of the flange of the forward side member to determine the thickness of the material, in accordance with the service bulletin. a. If the measurement of the forward side member is 0.031 inches or more, no further action is required. b. If the measurement of the forward side member is less than 0.031 inches, rework the service door forward side member, prior to further flight, in accordance with the service bulletin. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to theManager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6560, AD 90-08-04) becomes effective on May 4, 1990.
2012-24-04: We are adopting a new airworthiness directive (AD) for GA 8 Airvan (Pty) Ltd Models GA8 and GA8-TC320 Airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 burnt electrical connectors leading to the left-hand wingtip pitot heater, which may result in loss of airspeed indication. We are issuing this AD to require actions to address the unsafe condition on these products.
98-13-21: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A Olympus 593 series turbojet engines. This action requires initial and repetitive visual inspections of the low pressure (LP) shaft signal system for cable wear and refurbishment of the LP shaft signal system when the cable is found frayed, or at every engine shop visit, whichever occurs first. This amendment is prompted by reports of frayed rear cables in the LP shaft signal system. The actions specified in this AD are intended to prevent LP shaft signal system failure, which could result in an LP turbine overspeed, burst, uncontained engine failure, and damage to the aircraft in the event of a LP shaft failure. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of July 10, 1998. Comments for inclusion in the Rules Docket must be received on or before August 24, 1988.
2012-23-12: We are superseding an existing airworthiness directive (AD) for all Turbomeca S.A. Arriel 1E2, 1S, and 1S1 turboshaft engines. That AD currently requires a one-time inspection and torque check of the 3- way union plug installed on all fuel control units (FCUs). This new AD requires the same actions. This AD also requires reduction of the applicability to certain FCUs and references an updated service bulletin containing additional detailed information to identify the non-compliant ``red disk.'' This AD also requires replacement of the plug before further flight if it is found to be non-compliant, and prohibits installation of FCUs that have not passed the 3-way union plug inspection and torque check. This AD was prompted by Turbomeca S.A. informing us that FCUs manufactured, repaired, or overhauled after March 31, 2008, do not require inspection. We are issuing this AD to prevent fuel leaks, which could result in a fire and damage to the helicopter.
2012-24-02: We are adopting a new airworthiness directive (AD) for all Stemme GmbH & Co. KG Models S10, S10-V, and S10-VT powered sailplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 unapproved rubber hoses installed in the engine fuel, oil, and cooling systems, which could lead to a system leak and result in an engine fire. We are issuing this AD to require actions to address the unsafe condition on these products.
98-13-11: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes. This action requires modifying the airplane by incorporating Raytheon Kit No. 129-5200-1, "Ground Fine Switch Installation Kit". This action is the result of design analysis during certification of 5.5 degree approach landings of the Model 1900D airplanes. The actions specified by this AD are intended to prevent a loose or misrigged ground fine switch, which could result in very hard landings causing structural damage to the airplane and possible passenger injury.
2012-24-03: We are superseding an existing airworthiness directive (AD) for all Turbomeca S.A. Arriel 1A, 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K, 1K1, 1S, and 1S1 turboshaft engines. That AD currently requires initial and repetitive visual inspections for erosion caused by dust ingestion and, if necessary, cleaning of the gas generator (module M03). This new AD requires determining the engine history; performing a one-time visual inspection of the axial compressor for erosion; performing initial and repetitive cleaning of the gas generator hollow shaft; and replacing the rear bearing if the amount of dust collected during cleaning exceeds 8 grams. This AD also includes an optional terminating action. This AD was prompted by in-service experience which has shown that dust inside the gas generator hollow shaft may be found when the axial compressor wheel has less erosion than initially assessed. We are issuing this AD to prevent an unbalance of the gas generator rotating assembly,which may lead to gas generator rear bearing failure, and uncommanded engine shutdown.
75-16-10: 75-16-10 BEECH: Amendment 39-2296. Applies to 95-55, 95-A55, 95-B55, 95-B55A, 95-B55B, 95-C55, 95-C55A, D55, D55A, E55, E55A, 58, 58A, 56TC, A56TC, 95, B95, B95A, D95A and E95 (Serial Numbers listed below). Compliance: Required as indicated on specific models and serial numbers unless previously accomplished. To prevent failure of elevator trim tab systems, accomplish the following as specified: A) On Beech Models 95-55, 95-A55, 95-B55 and 95-B55A, serials TC-1 through TC-1143 except TC-350; 95-B55B (T-42A), serials TF-1 through TF-65; 95, B95, B95A, D95A and E95, serials TD-2 through TD-721; 95-C55, 95-C55A, D55 and D55A, serial TC-350 and TE-1 through TE-617; 56TC, serials TG-1 through TG-69, within 25 hours time in service after the effective date of this AD, unless otherwise complied with, inspect the elevator trim tab control rod and identify configuration/part number (swaged taper ends or 5/16" OD straight tubes). 1) If P/N 96-520012-9 assemblies (5/16"OD straight tubes with rivets in forward end) are installed: a) Ascertain whether "SI" is etched on a flat surface of the rod end fitting. If so, no further inspection is required. Part is to be replaced in accordance with following paragraphs of this AD. b) If "SI" is not etched on rod end fitting, remove the assembly and radiographically inspect the tube for eccentric reaming in the vicinity of the forward end fitting. Take radiographs from three equidistant directions (120 degrees apart). Before further flight, replace any tube where wall thickness at any one point is twice or more the thickness at the opposite side of the tube in accordance with the following paragraphs of this AD. 2) Remove all other P/N tube assemblies with swaged taper ends and inspect for cracks, looseness of end fittings, bending, or other signs of unairworthiness. Prior to further flight, replace any assembly found defective in accordance with the following paragraphs of this AD.B) On Beech Models 95-55, 95-A55, 95-B55 and 95-B55A, serials TC-1 through TC-1072 except TC-350 and TC-1071; 95-B55B (T-42A), serials TF-1 through TF-65; 95-C55, 95-C55A, D55 and D55A, serials TC-350, TE-1 through TE-542 except TE-521, TE-525 and TE-528 through TE-538; 56TC, serials TG-1 through TG-62 except TG-42, TG-45, TG-50, TG- 51 and TG-55; 95, B95, B95A, D95A and E95, serials TD-2 through TD-714 except TD-707, within 100 hours time in service after February 26, 1975, (effective date of AD 75-05-03), remove the two AN470AD3 rivets installed in the rod ends of P/N 45-524565-3 and 45-524565-5 elevator trim tab actuators and replace with P/N 96-524032 shoulder pins and MS20435F3-8 or MS20613-3C8 rivets. C) On Beech Models 95-55, 95-A55, 95-B55 and 95-B55A, serials TC-1 through TC-1143 except TC-350; 95-B55B (T-42A), serials TF-1 through TF-65; 95, B95, B95A, D95A and E95, serials TD-2 through TD-721, within the next 100 hours time in service after effective date of this AD, but not later than October 15, 1975, remove existing 5/16" diameter 45-526009 swaged, 96-526011 swaged, or 96-526012-9 5/16" OD elevator trim tab control rod tubes and install new 3/8" OD tube assemblies P/N 96-520013-1. On aircraft which have elevator tab assemblies, P/N 45-610005-120 and -121, installed, remove 5/16" OD elevator tube assembly P/N 96-520012-13, and install new P/N 96-520013-7 3/8" OD tube assembly; or, alternately install new elevator tab assemblies, P/N 45-610005-122 and -123. D) On Beech Models 95-C55, 95-C55A, D55 and D55A, serials TC-350 and TE-1 through TE-617; 56TC, serials TG-1 through TG-69, within the next 100 hours time in service after the effective date of this AD, but not later than October 15, 1975, remove existing 5/16" diameter 45-526009 swaged, 96-526011 swaged, or 96-526012-9 5/16" OD elevator trim tab control rod tubes and install a new 3/8" OD tube assembly P/N 96-520013-1. On aircraft which have elevator tab assemblies, P/N 96-610006-65 and -66 installed, remove 5/16" OD elevator tube assembly, P/N 96-520012-13, and install new 3/8" OD P/N 96-520013-7 tube assembly; or, alternately install new elevator tab assemblies P/N 96-610006-69 and -70. E) On Beech Models 95-B55 and 95-B55A, serials TC-1144 through TC-1379; D55, D55A, E55 and E55A, serials TE-618 through TE-837; 56TC and A56TC, serials TG-70 through TG-94, 58 and 58A, serials TH-1 through TH-120, within the next 100 hours time in service after the effective date of this AD, but not later than October 15, 1975, remove existing 96-526019 (basic) elevator trim tab tube assemblies having rod ends secured to the tube with 3/32 aluminum rivets and install new tube assembly, P/N 96-526021-9, having rod ends secured to the tube with 1/8" monel rivets or new elevator tab assemblies, P/N 96-610006-67 and -68. Alternately, replace four AN470AD3 rivets which attach the end fittings to the existing tube with four MS20615-3M or MS20613-3C rivets of appropriate length in accordance with Advisory Circular 43.13-1A. F) On Beech Models 95-B55 and 95-B55A, serials TC-1380 through TC-1775; 95- B55B (T-42A), serials TF-66 through TF-70; E55 and E55A, serials TE838 through TE-1005, 58 and 58A, serials TH-121 through TH-533, within the next 100 hours time in service after the effective date of this AD, but not later than October 15, 1975, remove existing 96-526019-5 or - 13 elevator tab tube assemblies having rod ends secured to the tube with 3/32 aluminum rivets and install new tube assembly, P/N 96-526021-1, having rod ends secured to the tube with 1/8" monel rivets. Alternately, replace the four AN470AD3 rivets which attach the end fitting to the existing rod with four MS20615-3M or MS20613-3C rivets of appropriate length in accordance with Advisory Circular 43.13-1A. G) Any alternate method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. H) Make a log book entry when complying with this AD. This entry must include date of compliance and method of compliance identified by AD paragraph and parts installed, signature, and number of certified agency/individuals performing the work. Beech Service Instructions No. 0610-152, Rev. II or later revision covers this subject. This AD supersedes Amendment 39-600 (AD 68-10-07) effective May 21, 1968 and Amendment 39-2097 (AD 75-05-03) effective February 26, 1975. This amendment becomes effective August 6, 1975.