Results
2012-26-10: We are adopting a new airworthiness directive (AD) for all Eurocopter France (Eurocopter) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365C, SA-365C1, SA-365C2, and SA-366G1 helicopters. This AD requires inspecting portions of the main gearbox (MGB) for the presence of sealing compound and corrosion. This AD was prompted by reports of corrosion on the main MGB casing lower area between the two servo-control anchoring fitting attachment ribs. An investigation determined that the corrosion was associated with sealing compound on the lower part of the fitting/casing attachment. The actions in this AD are intended to detect corrosion on the MGB casing, which could lead to a crack, failure of the MGB, and subsequent loss of control of the helicopter.
71-18-01: 71-18-01 CESSNA: Amendment 39-1275. Applies to 172 series airplanes (S/N 17248735 through 17256512). To provide correct information concerning fuel tank capacities, within the next 50 hours' time in service after the effective date of this AD, unless already accomplished, perform the following: A) Remove the existing placard on the fuel selector valve and install in its place either applicable Cessna P/N 0511167-20 placard or Cessna P/N 0500246-11 placard in accordance with Cessna Service Letter SE 68-12 dated March 12, 1968, or later FAA-approved revision, or any FAA-approved equivalent placard which would show usable fuel capacity of 18 gallons left tank, 18 gallons right tank, 36 gallons both and an off position. B) Revise the existing markings at the fuel filler necks to read: "FUEL 80/87 GRADE. TOTAL CAPACITY 19.5 GALLONS". (The operator may make and install the above markings with painted markings, using a minimum of 1/8 inch high letters.) This amendment becomes effective August 31, 1971.
98-21-22 R1: This amendment revises an existing airworthiness directive (AD), applicable to Pratt & Whitney JT9D series turbofan engines, that currently requires initial and repetitive eddy current inspections (ECI) of 14th and 15th stage high pressure compressor (HPC) disks for cracks, and removal of cracked disks and replacement with serviceable parts. This amendment revises the definition of a shop visit to make compliance less restrictive, and adds references to a Nondestructive Inspection Procedure attached to applicable service bulletins. This amendment is prompted by feedback from operators saying that the shop visit definition in the current AD made AD compliance unnecessarily restrictive. The actions specified by this AD are intended to prevent 14th and 15th stage HPC disk rupture, which could result in an uncontained engine failure and damage to the airplane.
2012-26-05: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter series airplanes, Model A330-200 series airplanes, Model A330-300 series airplanes, Model A340-200 series airplanes, and Model A340-300 series airplanes. This AD was prompted by a report of an in-flight turn back after the nose landing gear (NLG) did not retract after take-off. This AD requires repetitive overhaul of the NLG retraction actuator. We are issuing this AD to prevent failure of the retraction actuator, which could cause collapse of the NLG after touchdown and possible injury to flightcrew and passengers.
2006-11-16: The FAA is superseding an existing airworthiness directive (AD) for AlliedSignal, Inc. T5317A-1 turboshaft engines. That AD currently requires repetitive engine fuel pump pressure tests of certain fuel control regulator assemblies to determine if both fuel pumps in the fuel control regulator assemblies are producing fuel pressure. That AD also requires replacing the fuel control regulator assembly, if necessary. This AD requires initial and repetitive visual and dimensional inspections of fuel control regulator assembly main and secondary drive shaft and pump gear splines, installed in certain fuel control regulator assemblies. This AD also expands the engine applicability, and includes certain engines installed on helicopters certified under Sec. 21.25 or 21.27 of the Code of Federal Regulations (14 CFR 21.25 or 14 CFR 21.27). This AD results from several reports of loss of fuel flow from the engine fuel control regulator assembly due to failure of both main and secondary drive shaft and pump gear splines. We are issuing this AD to prevent in-flight engine failure and forced autorotation landing.
99-23-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Learjet Model 31, 31A, 35, 35A, and 60 airplanes, that requires a visual inspection of the spoiler actuators to determine the serial number of the spoiler actuators; and replacement of the spoiler actuators with new actuators, if necessary. This amendment is prompted by failure of a spoiler actuator piston rod during the first production flight of a Model 60 airplane due to an incomplete heat treatment process. The actions specified by this AD are intended to prevent failure of the spoiler actuator, which could result in the spoiler panel floating and inducing an uncommanded roll of the airplane.
75-16-14: 75-16-14 BRITISH AIRCRAFT CORPORATION: Amendment 39-2289. Applies to Model BAC 1-11, 200 and 400 Series airplanes. Compliance is required within the next 500 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible static inverter failure which could result in the loss of the A.C. emergency power supply to essential flight instruments, accomplish the following: (a) For airplanes which have not had BAC Modification 4535 incorporated, either - (1) Replace the installed Rotax static inverter, P/N U6705, with a serviceable Rotax static inverter, P/N U6705/1; or (2) Modify the installed Rotax static inverter, P/N U6705, in accordance with paragraph (c). (b) For airplanes which have had BAC Modification 4535 incorporated, either - (1) Replace the installed Rotax static inverter, P/N U6724, with a serviceable Rotax static inverter, P/N U6724/1; or (2) Modify the installed Rotax static inverter, P/N U6724, in accordance with paragraph (c). (c) Rotax static inverters, P/N U6705, may be converted to Rotax static inverters, P/N U6705/1, and Rotax static inverters, P/N U6724, may be converted to Rotax static inverters, P/N U6724/1, for compliance with paragraph (a)(2) or (b)(2) by - (1) Changing the R6 and R7 resistors on Printed Circuit Board No. 1 from 220 ohms/1.5 watt to 82 ohms/0.25 watt or 0.5 watt; and (2) Satisfying the functional tests for the modified static inverters as specified in Rotax Service Bulletin No. 24-420 at Revision 1, dated August 20, 1971 (Rotax Modification No. 4743 U) or an FAA-approved equivalent. (British Aircraft Corporation, Model BAC 1-11 Service Bulletin No. 24-PM 4992, Revision 1, dated November 8, 1971, refers to this same subject). This amendment becomes effective August 28, 1975.
2012-25-09: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-524G2-19; RB211-524G2-T-19; RB211-524G3-19; RB211-524G3-T-19; RB211-524H2-19; RB211-524H2-T-19; RB211-524H-36; RB211-524H-T-36; RB211-535E4-37; RB211-535E4-B-37; RB211-535E4-B-75; and RB211-535E4-C-37 turbofan engines. This AD was prompted by an investigation by RR concluding that certain intermediate-pressure (IP) turbine discs produced before 1997 by a certain supplier may contain steel inclusions. This AD requires removal of the affected IP turbine discs to inspect them for steel inclusions, and removal of the affected discs from service if they fail the inspection. This AD also requires removal from service of some IP turbine discs at reduced life limits. We are issuing this AD to prevent uncontained IP turbine disc failure, engine failure, and damage to the airplane.
2012-18-10 R1: We are revising an existing airworthiness directive (AD) for all GA200 (Pty) Ltd Models GA200 and GA200C 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 failure of the wing strut bolt through the main spar. We are issuing this AD to require actions to address the unsafe condition on these products.
2006-01-05: The FAA is adopting a new airworthiness directive (AD) for certain Honeywell International Inc., (formerly AlliedSignal, Inc., formerly Textron Lycoming, formerly Avco Lycoming) T53 turboshaft engines, installed on, but not limited to, Bell 204, Bell 205, Kaman K- 1200 series, Bell AH-1, and Bell UH-1 helicopters, certified under 14 CFR 21.25 or 14 CFR 21.27. This AD requires implementing reduced life limits for certain parts, using cycle counting methods, and using draw- down schedules to replace components that exceed the new limits. This AD results from the manufacturer informing us of test and analysis showing lower calculated service life limits for certain parts, than previously published. We are issuing this AD to prevent failure of certain compressor, gas producer, and power turbine rotating components, which could result in failure of the engine and possible damage to the helicopter.
73-12-04: 73-12-04 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1654. Applies to Viscount Model 810 Series Airplanes, which do not incorporate Modification G.1843. Compliance is required as indicated. To detect loose or sheared rivets on the airsteps hinged fairing operating link, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 475 hours' time in service prior to the effective date of this AD, and thereafter at intervals not to exceed 500 hours' time in service from the last inspection, inspect the 3/16 inch diameter rivets on the airsteps hinged fairing operating link for looseness and shearing. (b) If sheared or loose rivets are found during an inspection required by paragraph (a), before further flight, either - (1) Replace the sheared or loose rivets with serviceable rivets of the same type, that are approved for installation in the assembly, and continue to inspect inaccordance with paragraph (a); or (2) Incorporate Modification G.1843, dated September 22, 1961, or an FAA- approved equivalent. (c) The repetitive inspections required by this AD may be discontinued after Modification G.1843 is incorporated. This amendment becomes effective July 1, 1973.
2012-25-10: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-300 series airplanes and Model A340-200 and -300 series airplanes. This AD was prompted by reports that, during a flight test, several spoiler servo-controls (SSCs) did not remain locked in the retracted position (hydraulic locking function) after manual depressurization of the corresponding hydraulic circuit. Loss of that locking function--which is ensured by a blocking valve--was caused by an internal leak from a sheared seal on the blocking valve. This AD requires inspecting to determine if certain SSCs are installed, performing an operational test of any affected SSC, and replacing if necessary. We are issuing this AD to prevent loss of the hydraulic locking function during take-off and go-around phases, which, in combination with malfunction of one engine, could result in reduced controllability of the airplane.
2012-25-08: We are adopting a new airworthiness directive (AD) for certain serial numbers (S/Ns) of Rolls-Royce plc (RR) RB211-Trent 768-60, 772- 60, and 772B-60 turbofan engines. This AD requires initial and repetitive on-wing or in-shop inspections of the high pressure/ intermediate pressure (HP/IP) turbine bearing support oil feed tube outer heat shield. This AD also requires installation of a revised HP/ IP turbine bearing support structure as terminating action to the repetitive inspections of the HP/IP turbine bearing support oil feed tube outer heat shield. This AD was prompted by a report of high oil consumption due to an oil leak from the HP/IP turbine bearing support oil feed tube. We are issuing this AD to prevent failure of the HP turbine disc, uncontained engine failure, and damage to the airplane.
75-24-14: 75-24-14 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2440. Applies to Alouette Helicopters SE-3130, SE-313B, SA-315B, SE-3160, SA-316B, SA- 316C, SA-3180, SA-318B, SA-318C, and SA-319B equipped with main rotor hydraulic dampers P/N 3130S.13.60.000. Compliance is required as indicated, unless already accomplished. To prevent excessive vibration or ground resonance, accomplish the following: (a) Prior to October 30, 1975, modify and reidentify main rotor hydraulic dampers P/N 3130S.13.60.000 in accordance with subparagraphs 2B(1), 2B(2), and 2(c) of Lama Service Bulletin No. 65.20 dated July 4, 1975, for Model SA-315B and Alouette Service Bulletin No. 65.107 dated July 4, 1975, for the other designated models, or equivalents approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, New York, N.Y. 09667. (b) Prior to further flight, for Models SA-3160, SA-316B, SA-316C, andSA-319B, remove the placard required by AD 75-17-30, if installed, and install a temporary placard on the instrument panel, in full view of the pilot, reading as follows: "Maximum density altitude: 8200 feet". Temporary placard may be removed upon accomplishment of paragraph (a) of this AD. (Alouette Service Bulletin No. 01.39 also refers to paragraph (b) of this AD). This AD supersedes Amendment 39-2335 (40 FR 33010), AD 75-17-30. This amendment is effective upon publication in the FEDERAL REGISTER as to all persons except those persons to whom it was made immediately effective by telegram dated September 30, 1975, which contained this amendment.
2003-09-05: This amendment adopts a new airworthiness directive (AD) for Schweizer Aircraft Corporation (Schweizer) Model 269D helicopters. This action requires inspecting each aluminum horizontal stabilizer endplate (endplate) and the attach angles for cracks, fretting, and endplate bending. If fretting is found, as indicated by a powder residue adjacent to a rivet head, installing an inspection hole in the horizontal stabilizer and inspecting the internal structure is required. Replacing unairworthy parts is required before further flight. Finally, reporting any cracked or bent endplate, any cracked attach angles, or fretting to the FAA is required. This amendment is prompted by reports of loose endplates, and one report of an endplate separating from the helicopter during flight. The actions specified in this AD are intended to prevent loss of an endplate during flight, which could strike the tail rotor and result in loss of control of the helicopter.
2012-25-07: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GIV-X airplanes. This AD requires performing a modified system power-on self test (SPOST) of the flap/stabilizer electronic control unit (FSECU), and revising the airplane flight manual to incorporate these test procedures into the daily preflight check. This AD was prompted by [[Page 74580]] reports indicating that the FSECU does not detect failures of the brake feature within the horizontal stabilizer electric motor unit (HSEMU), or failures of drive solenoids for hydraulic valves within the flap hydraulic control module (FHCM) during the SPOST. We are issuing this AD to detect and correct such failures, which could result in runaway horizontal stabilizer pitch trim system and consequent loss of pitch control.
49-49-01: 49-49-01 LOCKHEED: Applies to All Model 49 Series Aircraft Equipped With Eclipse- Pioneer Model PB-10 Automatic Pilots. Compliance required prior to reconnection in aircraft. Prior to reconnection in the aircraft of the Eclipse-Pioneer Model PB-10 automatic pilot, it is necessary to modify the installation to include provisions designed to safeguard the aircraft in the event of malfunctioning of the autopilot. This modification has been determined to consist of the following interdependent changes: Modify the master direction indicator and wiring at the autopilot controller plug and amplifier to change the direction signal from the rudder channel to the aileron channel; install resistors in series with the variable phase of aileron, rudder and elevator servo motors to reduce servo forces; install aileron servo disconnect interlock switch and change wiring to this switch from the existing rudder servo disconnect interlock switch. An acceptable method of accomplishingthis modification is described in LAC Service Bulletin No. 49/SB-576. This supersedes AD 49-36-01.
2012-21-52: We are publishing a new airworthiness directive (AD) for Agusta Model AW139 helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting the pilot's and co-pilot's collective and cyclic control sticks for correctly installed attaching hardware. This AD is prompted by a report of an incorrectly installed pilot's collective stick, pilot's cyclic stick, and co-pilot's cyclic stick. These actions are intended to prevent detachment of the cyclic or collective control stick, and subsequent loss of control of the helicopter.
48-03-05: 48-03-05 CURTISS-WRIGHT Applies to all C-46 Series aircraft. Compliance required by March 1, 1948. To eliminate hydraulic leaks which can cause a fire, hydraulic tube P/N 20-575-1116-64 located at fuselage Station 50.5 between the brake accumulator and brake metering valve, should be inspected for evidence of chafing on tube assembly tension arm P/N 20-530-1130-1. If insufficient clearance exists, the hydraulic lines must be rerouted and damaged lines replaced.
2005-04-10: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CT58-140-1, CT58-140-2, and surplus military T58-GE-5, -10, -100, and -402 turboshaft engines with certain serial numbers (SNs) of stage 1 compressor disks, part number (P/N) 5001T20P01, installed. This AD requires removing certain stage 1 compressor disks from service before reaching a reduced low-cycle- fatigue (LCF) life limit for those affected disks of 2,100 hours time- since-new (TSN) or by December 31, 2008, whichever occurs first. This AD results from two reports of low blade tip clearances in the compressor. We are issuing this AD to prevent LCF cracking and failure of the stage 1 compressor disk, an uncontained engine failure, and damage to the helicopter.
2012-23-11: We are adopting a new airworthiness directive (AD) for Erickson Air-Crane Incorporated (Erickson) Model S-64F helicopters. This AD requires inspecting for cracking or working rivets in each left and right splice fitting (transition fitting), the pylon bulkhead assembly-canted (bulkhead assembly), and the pylon steel strap (strap). This AD was prompted by several reports of cracking in the transition fittings, the bulkhead assembly, and the pylon. The actions specified by this AD are intended to detect cracking in the rotary rudder boom or pylon due to fatigue, and to prevent failure from static overload and subsequent loss of control of the helicopter.
2012-24-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD requires ensuring that lockwire is installed correctly on the engine fuel feed manifold couplings. This AD also requires inspecting the assembly of the engine fuel feed manifold rigid and full flexible couplings. This AD was prompted by reports of fuel leaks due to improperly assembled engine fuel feed manifold couplings. We are issuing this AD to detect and correct improperly assembled couplings, which could result in fuel leaks and consequent fuel exhaustion, engine power loss or shutdown, or leaks on hot engine parts that could lead to a fire.
47-41-05: 47-41-05 BELL: (Was Mandatory Note 17 of AD-1H-2.) Applies to All Models in 47B Series, Through Serial Number 78. Compliance required at next 100-hour inspection. In order that the bearings will be securely locked in the gimbal ring, the fiber bearing seals should be replaced with steel bearing seals, P/N 27-120-127-1. This alteration is covered by Bell Service Bulletin 47C30 dated July 10, 1947.
99-22-10: 99-22-10 GENERAL ELECTRIC AIRCRAFT ENGINES: Amendment 39-11388. Docket 98-ANE-62-AD. Issued October 18, 1999. Applicability: General Electric Aircraft Engines (GEAE) Models CF34-1A, -3A, -3A1, and -3A2 turbofan engines, installed on but not limited to Canadair aircraft models CL-600-2A12, -2B16, and -2B19. NOTE 1: This airworthiness directive (AD) applies to each engine 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 engines 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 (b) 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. Compliance: Required as indicated, unless accomplished previously. To prevent high pressure compressor (HPC) spool and disk cracking, which could result in an uncontained engine failure and damage to the aircraft, accomplish the following: (a) Remove from service the following HPC spools and disks prior to accumulating cycles in service beyond new, reduced cyclic life limits, and replace with a serviceable part, as follows: (1) For forward HPC spools, part number (P/N) 6078T56P01, which have accumulated fewer than 6,000 cycles since new (CSN) on the effective date of this AD, remove prior to accumulating 6,000 CSN. (2) For forward HPC spools, P/N 6078T56P01, which have accumulated 6,000 or more CSN on the effective date of this AD, remove at the next shop visit after the effective date of this AD, but prior to accumulating 12,000 CSN. (3) For the purpose of this AD, engine shop visit is defined as engine disassembly that includes separation of the compressor section from the fan section front frame and from the combustion section combustion chamber frame. (4) For stage 9 HPC disks, P/N 6087T01P03 or 6087T01P04, remove prior to accumulating 20,000 CSN. (5) For rear HPC spools, P/N 5087T46P01 or 5087T46P02, remove prior to accumulating 17,000 CSN. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) Special flight permits may be issued in accordance withsections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (d) This amendment becomes effective on December 27, 1999.
2012-23-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of a crack found in the fuselage skin under the aft drain mast. This AD requires a detailed inspection for cracking and corrosion of the channel and fillers adjacent to the drain mast bolts, an inspection to determine the location of the bonding strap, a measurement of the washers under the drain mast bolts, and related investigative actions and repair if necessary. We are issuing this AD to detect and correct cracking in the fuselage skin and internal support structure, which could result in uncontrolled decompression of the airplane.