Results
2012-22-11: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron (BHT) Model 412, 412EP, and 412CF helicopters. This AD requires a repetitive inspection of the collective lever for a crack, and if there is a crack, before further flight, replacing the collective lever with an airworthy collective lever. This AD was prompted by a reported failure of a collective lever. The actions are intended to detect a crack in the collective lever, which could lead to failure of the collective lever and subsequent loss of control of the helicopter.
99-20-12: This amendment adopts a new airworthiness directive (AD), applicable to MD Helicopters, Inc. Model 369D, 369E, 369FF, 500N, and 600N helicopters, that requires replacing the oil cooler blower bracket (bracket). This amendment is prompted by three reports of cracked brackets. The actions specified by this AD are intended to prevent failure of a bracket, loss of cooling of engine oil and transmission oil, and a subsequent forced landing.
67-19-04: 67-19-04 MARTIN: Amdt. 39-432, Part 39, Federal Register June 15, 1967. Applies to Type 202, 202A and 404 Airplanes Incorporating Engine Mount, P/N's A10100, A10100-9, 2021C11039-9, A16647-81, 404-5000004, 404-5000004-59, 404-5000005, or 404-5000005-29. Compliance required as indicated. To detect cracks and corrosion in the engine mounts, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the last 100 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection; visually inspect the engine mount tubular members and welds for cracks, using a glass of at least 10-power, or use an FAA- approved equivalent inspection. If a crack is found comply with (c) before further flight. (b) Within the next 250 hours' time in service after the effective date of this AD, unless already accomplished within the last 750 hours' time in service, and thereafter at intervals not to exceed 1000 hours' time in service from the last inspection, or one (1) year whichever occurs first, inspect the engine mount tubular members and welds for external and internal cracks and corrosion, using both Magnaflux and X-ray or FAA-approved equivalent inspections. Remove paint and sandblast the engine mount prior to inspecting, or use an FAA-approved equivalent method. The sandblasting operation should be limited to the removal of any light rust or other superficial discolorations as necessary to give a clean surface to conduct Magnaflux inspection. If a crack is found comply with (c) before further flight. Engine mounts inspected within the last 750 hours' time in service using Magnaflux and X-ray, or FAA-approved equivalent inspections, but without sandblasting need not be reinspected before 1000 hours' of time in service from such inspection. (c) If a crack is found in the weld metal or in any tube between welds, and the crack is parallel to the tube axis, repair or replace the cracked part in accordance with the procedures outlined in the latest FAA-approved revision of the applicable Martin structural repair manual, or with an FAA-approved equivalent repair, or replace the cracked part with a part of the same part number that has been inspected in accordance with (b) and found free of cracks and corrosion, or with an FAA-approved equivalent part. If a crack is found in any tube wall, and the crack is transverse to the tube axis, replace the entire engine mount with a part of the same part number that has been inspected in accordance with (b) and found free of cracks and corrosion, or with an FAA-approved equivalent part. If a crack is found which is not identified above, approval for continued use of the engine mount must be obtained from the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Substantiating data must be submitted along with the request. (d) The repetitive inspection interval specified in paragraph (a) may be increased to 350 hours' time in service, and the repetitive inspection interval specified in paragraph (b) may be increased to 2500 hours' time in service or two (2) years, whichever occurs first, on aircraft whose engine mounts are treated internally at the next required inspection with hot linseed oil. The liquid shall be applied through holes drilled therein, or by immersing the part in a bath of the liquid, or FAA-approved equivalent method. All excess holes must be closed with cadmium- plated or zinc-plated self-tapping screws. (e) Equivalent inspections and repairs may be approved by an FAA maintenance inspector. Equivalent parts, Structural Repair Manual revisions, and internal treatment methods specified in paragraph (d), must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (f) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance timesspecified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This supersedes AD 66-12-01. This amendment effective June 20, 1967.
47-32-15: 47-32-15 SIKORSKY: (Was Mandatory Note 1 of AD-2H-1.) Applies to Model S-51 Helicopters. Compliance required prior to next flight. Inspect the chain and sprockets of the control system for an accumulation of excessive grease and foreign matter. Excessive grease and any foreign matter adhering to the chain and sprockets should be removed prior to the next flight in order to prevent possible malfunctioning of the flight control system. The recommended procedure as contained in the Sikorsky Service Information Circular No. 17 dated June 2, 1947, should be followed at the first disassembly of these parts.
2003-17-03 R1: We are revising an existing airworthiness directive (AD) for certain Piaggio Aero Industries S.p.A. Model P-180 airplanes. That AD currently requires replacement of any firewall shutoff or crossfeed valve with a serial number in a certain range even if it has been previously modified. The way the applicability was written includes valves that should not be affected and are not included in the referenced service information. This AD requires [[Page 67765]] the same actions as the current AD, but only affects those firewall shutoff valves referenced in the referenced service information. We are issuing this AD to clarify the affected parts required to correct the unsafe condition on these products.
97-21-08: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company CT58 series turboshaft engines, that requires removal from service of certain stage 1 and 2 forward cooling plates, and stage 2 aft cooling plates, and replacement with serviceable parts. This amendment is prompted by reports of certain cooling plates forged with contaminated alloy that could reduce the lives of the parts. The actions specified by this AD are intended to prevent cooling plate fracture, which could result in a contained engine failure, and an inflight engine shutdown.
2011-21-07 R1: We are revising an existing airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes; all Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes; all Model CL-600-2D15 (Regional Jet Series 705) airplanes; and all Model CL-600-2D24 (Regional Jet Series 900) airplanes. That AD currently requires replacing certain water accumulator assemblies having a certain part installed on the pitot and static lines of the air data computer (ADC). This new AD corrects an erroneous service document number and removes the other erroneously cited service document from that AD. This new AD was prompted by an error that was discovered in one service document number, and a determination that credit for accomplishing actions in another erroneously cited service document should be removed from that AD. We are issuing this AD to prevent pitot-static tubing from becoming partially or completely blocked by water, which could result in erroneous airspeed and altitude indications and consequent loss of control of the airplane.
75-17-36: 75-17-36 BALLOON WORKS, HOT AIR BALLOONS: Amendment 39-2326. Applies to Models Firefly 6, 6B, and 7 with burner S/N 510 through 562. Before next flight, accomplish the following or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Southern Region. To avoid separation due to a possible brass nipple failure, install safety wire extending from each of the three corners of the bottom plate to the lower portion of the upper Rego valve body. Assure wires are uniformly tightened. Within the next five hours of time in service from the effective date of this AD, accomplish the following: 1. Disconnect main burner tubes from manifold. 2. Drill out nine rivets holding pan to the bottom plate. 3. Unhook three burner support springs. 4. Remove upper burner assembly from lower burner assembly. 5. Unscrew nuts to remove pilot light tubes. 6. Clamp square section of Rego valve in vise. 7. Unscrew and remove burner manifold. 8. Inspect nipple. If nipple is steel, reassemble the burner,* if nipple is brass, proceed through the following steps. 9. Unscrew nipple with pipe wrench. 10. Replace brass nipple with steel nipple, Balloon Works P/N A4032B. 11. Reassemble in the reverse order. Safety wire is not required after steel nipple is installed. *Use teflon tape or pipe dope type sealant on nipple threads. This amendment is effective August 13, 1975, and was effective on receipt for all recipients of the air mail letter dated July 24, 1975 which contained this amendment.
2012-22-06: We are adopting a new airworthiness directive (AD) for Aeronautical Accessories, Inc. (AAI) high landing gear forward crosstube assemblies (crosstubes) installed on Agusta S.p.A. (Agusta) Model AB412 and AB412EP; and Bell Helicopter Textron, Inc. (Bell) Model 205A, 205A-1, 205B, 212, 412, 412CF, and 412EP helicopters during production or based on a supplemental type certificate (STC). This AD requires counting and recording the total number of landings for the crosstubes, and inspecting the crosstubes and replacing them if a crack or other damage exists. This AD was prompted by two reports from the field of failed crosstubes. The actions are intended to prevent failure of a crosstube, collapse of the landing gear, and subsequent loss of control of the helicopter.
97-19-17: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company CT58 series turboshaft engines, that requires removal from service of certain compressor rear shafts, initial and repetitive inspections of specific critical rotating parts, and replacement if found cracked, until those parts are removed from service and replaced with improved design parts. This amendment is prompted by a stage 2 turbine wheel incident in 1993 which resulted in an increased awareness of small features on critical rotating parts which could affect part life. The actions specified by this AD are intended to prevent fatigue cracking on specific critical rotating parts, which could result in failure of the part, causing an uncontained engine failure and damage to the aircraft.