Results
94-18-08: This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Company and Hughes Helicopters, Inc. Model 369, 369A (OH-6A), 369D, E, F, FF, H, HE, HS, and HM series helicopters, that requires daily preflight checks and 100 hours time-in-service (TIS) inspections for tail rotor blade abrasion strip (abrasion strip) debonding until abrasion strip rivets (rivets) are installed. This amendment also supersedes a Priority Letter AD that currently requires installation of rivets, corrects tail rotor blade part numbers listed in the previous AD, and retains the daily preflight checks of the previous AD until rivets are installed to secure the abrasion strip. This AD provides a terminating action for the abrasion strip debonding and also seeks to clear up any confusion among operators caused by having a published AD and a Priority Letter that are applicable to the same helicopter part. This AD replaces both of those documents. Thisamendment is prompted by an accident resulting from the separation of an abrasion strip from a tail rotor blade and subsequent tail rotor separation. The actions specified by this AD are intended to prevent loss of the abrasion strip, separation of the tail rotor, and subsequent loss of control of the helicopter.
2008-03-16: We are adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to inspect the rudder, aileron, and rudder-aileron interconnect rigging; correct any out-of-rig condition; replace the attaching hardware for the rudder-aileron interconnect arm; and report any out-of-rig condition found. This AD results from a jamming of the aileron and rudder controls on a Model SR20 airplane, which resulted in loss of rudder and aileron flight controls. We are issuing this AD to prevent the possibility of jamming of the rudder-aileron interconnect system, which may result in loss of rudder and aileron flight controls.
2001-13-19: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 series airplanes, that requires revising the Bombardier maintenance program to incorporate repetitive inspections to detect fatigue cracking in certain structures; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information issued by a foreign airworthiness authority. The actions specified by this AD are intended to ensure that fatigue cracking of certain principal structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
2001-13-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes and Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes, that requires revising the Airplane Flight Manual to prohibit the airplane from being moved during inertial reference unit alignment. The actions specified by this AD are intended to prevent a loss of positioning data and a display of incorrect attitude data to the flight crew, which could result in severe consequences to the airworthiness of the airplane if operated under flight conditions with no visual reference. This action is intended to address the identified unsafe condition.
81-19-08: 81-19-08 GENERAL ELECTRIC: Amendment 39-4219. Applies to all General Electric Model CF6-6 series turbofan engines installed in McDonnell Douglas DC10-10 aircraft containing low pressure turbine rotor stage 2 disks, P/Ns 9690M77P03, 9690M77P04, 9690M77P09, 9690M77P11, and 9690M77P13. Compliance required as indicated. To prevent possible low cycle fatigue failure of these disks, the life limits have been reduced below the figures currently approved. Remove from service low pressure turbine rotor stage 2 disks prior to reaching the revised life limits listed below or within the next 25 cycles in service after the effective date of this AD, whichever comes later. Disk Part Number Previous Life Limit/Cycles Revised Life Limit/Cycles 9690M77P03 27,000 11,500 9690M77P04 27,000 11,500 9690M77P09 27,000 11,500 9690M77P11 27,000 11,500 Serial Numbers MP0A0727 through MP0A2215 9690M77P11 27,000 9,300 All other serial numbered disks9690M77P13 27,000 10,000 NOTE: General Electric CF6-6 Service Bulletin 72-786 pertains to this subject. This amendment becomes effective on September 21, 1981.
2018-17-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by reports of failures of the lip heater assemblies of the inlet ice protection system of the cabin air compressor (CAC) due to chafing. This AD requires changing the airplane electrical connectors and the routes of certain wire bundles, and installing new or modified left and right CAC inlet duct assemblies. We are issuing this AD to address the unsafe condition on these products.
2008-03-10: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 525, 525A, and 525B airplanes. This AD requires you to inspect the lower wing skin structure, forward wing spar, lower fuselage skin, fairings, and the external fairing frames for corrosion; repair any damage found; apply a corrosion inhibitive sealant to the fuselage fairings before reinstalling; and disable the cockpit mounted pilot relief tube. This AD results from leaking of the cockpit mounted pilot relief tube, which caused corrosion of the airplane structure. We are issuing this AD to detect and correct any damage from corrosion of the airplane structure. Corrosion of the airplane structure could cause structural degradation and lead to structural failure of the airplane with consequent loss of control.
2020-19-04: The FAA is adopting a new airworthiness directive (AD) for Leonardo S.p.a. (Leonardo) Model AB139 and AW139 helicopters. This AD requires removing certain main gearbox (MGB) input modules from service. This AD was prompted by the discovery that a batch of duplex bearings, which are installed on the MGB input modules, are defective. The actions of this AD are intended to address an unsafe condition on these products.
94-17-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections of the inboard and outboard strut chords, stiffeners, and web to detect cracks and loose fasteners; repair of the chords, stiffeners, or web, if necessary; and replacement of any loose fastener. This amendment is prompted by reports of fatigue cracks and loose fasteners found in the forward lower spar web of the inboard strut on Model 747 series airplanes equipped with Pratt & Whitney JT9D-3 and JT9D-7 series engines. The actions specified by this AD are intended to prevent separation of the strut from the wing of the airplane due to fatigue cracking.
2008-03-05: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747- 200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes; and Model 767-200 and -300 series airplanes; equipped with certain Goodrich evacuation systems. For certain airplanes, this AD requires replacing the evacuation system shear-pin restraints with new ones. For certain other airplanes, this AD requires an inspection for manufacturing lot numbers; and a general visual inspection of the shear-pin restraints for discrepancies, and corrective actions if necessary. This AD results from several reports of corroded shear-pin restraints that prevented Goodrich evacuation systems from deploying properly. We are issuing this AD to prevent failure of an evacuation system, which could impede an emergency evacuation and increase the chance of injury to passengers and flightcrew during the evacuation.
2001-13-22: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A military), and -40 series airplanes; and Model MD-10-10F and MD-10-30F series airplanes, that currently requires, among other actions, performing repetitive ultrasonic inspections of the attaching bolts on the inboard and outboard support on the inboard and outboard flap assembly to detect failed bolts, or verifying the torque of the attaching bolts on the inboard support on the outboard flap; and follow-on actions. This amendment, among other actions, adds a requirement to verify the torque of the attaching bolts on the outboard support on the inboard and outboard flaps, and allows repetitive torque verifications. This amendment is prompted by a review that revealed inadvertent omission of a requirement. The actions specified by this AD are intended to prevent in-flight loss of inboard and outboard flap assemblies due to failure ofH-11 attaching bolts, which could result in reduced controllability of the airplane.
2001-13-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires a one-time inspection to find wire chafing of the left and right engine fuel shutoff valve wire bundles at Power Plant Station 278 on each engine strut, and repair if necessary. This amendment also requires replacement of three wire support brackets with improved wire support brackets. This amendment is prompted by reports that such wire support brackets failed due to fatigue, which subsequently caused the fuel shutoff valve wire to chafe and to experience a short circuit. The actions specified by this AD are intended to prevent such conditions, which could result in either the possible ignition of fuel vapors in a flammable leakage zone or in the inability to stop the flow of fuel in the event of an engine fire.
94-16-04: This amendment adopts a new airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH55A series helicopters, that requires a one-time visual inspection to detect missing or damaged tail rotor pedal bulkhead gussets (gussets), loose or missing gusset rivets, and initial installation of missing gussets or replacement of damaged gussets and rivets, if necessary. This amendment is prompted by reports of missing or damaged tail rotor pedal bulkhead gussets and loose or missing gusset rivets. The actions specified by this AD are intended to prevent failure of the tail rotor pedal support structure that could result in loss of tail rotor control and subsequent loss of control of the helicopter.
2008-03-09: The FAA is adopting a new airworthiness directive (AD) for CFM International, S.A. CFM56-7B series turbofan engines. This AD requires revising the Airworthiness Limitations Section (ALS) in the Engine Shop Manual (ESM) and the air carrier's approved continuous airworthiness maintenance program (CAMP) to add mandatory inspections of certain low pressure turbine rear frames (TRFs) to the ALS or CAMP. This AD results from a refined lifing analysis by the engine manufacturer that shows the need to identify an initial threshold for inspecting certain TRFs. We are issuing this AD to prevent failure of the TRF from low-cycle fatigue cracks. Failure of the TRF could result in engine separation from the airplane, which could lead to loss of control of the airplane.
2001-13-18: This document supersedes Airworthiness Directive (AD) 99-12-02, which currently requires flight and operating limitations on Raytheon Aircraft Corporation (Raytheon) Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) airplanes. AD 99-12-02 resulted from a report of an in-flight separation of the right wing on a Raytheon Beech Model A45 (T-34A) airplane. The AD was issued as an interim action until the development of FAA-approved inspection procedures. Raytheon has developed procedures to inspect the wing spar assemblies of the above-referenced airplanes. This AD requires repetitive inspections of the wing spar assembly for cracks with replacement of any wing spar assembly found cracked (unless the spar assembly has a crack indication in the filler strip where the direction of the crack is toward the outside edge of the filler strip). This AD also includes a reporting requirement of the results of the initial inspection and maintains the flight and operating restrictions required by AD 99-12-02 until accomplishment of the initial inspection. The actions specified by this AD are intended to prevent wing spar failure caused by fatigue cracks in the wing spar assemblies and ensure the operational safety of the above-referenced airplanes.
2020-06-16: The FAA is superseding Airworthiness Directive (AD) AD 2017- 03-02 for certain Rolls-Royce, Deutschland Ltd. & Co. KG RB211 Trent 768-60, 772-60, and 772B-60 model turbofan engines. AD 2017-03-02 required initial and repetitive ultrasonic inspections (UIs) of the affected low-pressure (LP) compressor blades. This \n\n((Page 17739)) \n\nAD requires initial and repetitive UIs of the affected LP compressor blades and, depending on the results of the UIs, their replacement with a part eligible for installation. This AD was prompted by LP compressor blade partial airfoil release events. The FAA is issuing this AD to address the unsafe condition on these products.
94-17-10: This amendment adopts a new airworthiness directive (AD), applicable to all de Havilland Model DHC-8 series airplanes, that requires removal of the aluminum or brass hardware in the firewall terminal block and battery shunt cable assemblies and replacement with steel hardware. This amendment is prompted by the results of an investigation, which revealed that corroded aluminum washers in the DC firewall terminal block and battery shunt cable assemblies may loosen the electrical connections. The actions specified by this AD are intended to prevent interruption of DC electrical power due to connections that may have loosened from corrosion.
2008-03-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A leakage in the area of a plastic T-connector was found during a daily pre-flight check. The investigation has shown a crack in the centre part of this connector. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2001-13-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Model A310 and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (collectively called A300-600) series airplanes, that requires replacement of the ejection jack on the ram air turbine (RAT). The actions specified by this AD are intended to prevent the ejection jack on the RAT from failing when the RAT is deployed at high airspeeds, leading to a loss of ability to properly restrain the movement of the RAT, possibly resulting in damage to the RAT itself and to other airplane components. In the event of an emergency, failure of the ejection jack on the RAT could also result in a reduction of hydraulic pressure or electrical power on the airplane. This action is intended to address the identified unsafe condition.
2020-04-20: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-400 series airplanes. This AD was prompted by reports of wear on fuel couplings, bonding springs, and sleeves as well as fuel tube end ferrules and fuel component end ferrules. This AD requires repetitive inspections of certain parts for discrepancies that meet specified criteria, and replacement as necessary; repetitive inspections of certain parts for damage and wear, and rework of parts; and electrical bonding checks of certain couplings. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. For certain airplanes, this AD allows a modification that would terminate the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
83-15-08 R1: 83-15-08 R1 BRITISH AEROSPACE: Amendment 39-4697 as revised by Amendment 39- 6255. Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated unless previously accomplished. To prevent structural failure of the fuselage, accomplish the following: A. Perform initial and repetitive visual and eddy current inspections of fuselage skin lap joints for cracks and loose rivets at the intervals shown in Table I of this AD, in accordance with Section 2, of the Accomplishment Instructions, of British Aerospace Alert Service Bulletin 53-A-PM5726, Issue 3, dated May 26, 1988. B. Repair any identified cracks or loose rivets prior to further flight, in accordance with paragraph 2.4.2 of British Aerospace Alert Service Bulletin 53-A-PM5726, Issue 3, dated May 26, 1988; or Chapter 53-02-0, Figure 89, of the BAC 1-11 Structural Repair Manual, whichever is appropriate; or in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. 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 the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of 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, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined atthe 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 AD revises AD 83-15-08, Amendment 39-4697. This amendment (39-6255, AD 83-15-08 R1) becomes effective on August 7, 1989. TABLE I Airplanes Affected AD 83-15-08 Previously Complied With? Initial Inspection Threshold for this AD Repetitive Inspection Interval Airplanes operated only at standard cabin pressure of 7.5 psi max cabin differential pressure NO Whichever occurs later: -Within 1,250 landings after September 6,1983 (effective date of AD 83-15-08); or For airplanes with less than 50,000 landings: Visual Inspection: -Every 1,250 landings -Upon accumulating the number of landings determined by Figure 1 of British Aerospace Alert Service Bulletin 53-A-PM5726, Revision 3, dated May 26, 1988 Eddy Current Inspection: -Every 3,750 landings For airplanes with 50,000 or more landings: YES Visual Inspection: -Within 1,250 landings after the last visual inspection in accordance with AD 83-15-08 Eddy Current Inspection: -Within 3,750 landings after the last eddy current inspection in accordance with AD 83-15-08 Visual Inspection: -Every 1,875 landings Eddy Current Inspection: -Every 3,750 landings Airplanes operated at increased cabin pressure of 7.75 psi max cabin differential pressure NO Whichever occurs later: -Within 1,250 landings after September 6,1983 (effective date of AD 83-15-08); or -Upon accumulation of 35,000 landings. Visual Inspection: -Every 1,600 landings Eddy Current Inspection: -Every 3,200 landings YES Visual Inspection: -Within 1,600 landings after the last visual inspection in accordance with AD 83-15-08 Eddy Current Inspection: -Within 3,200 landings after the last eddy current inspection in accordance with AD 83-15-08 Airplanes operated at increased cabin pressure of 8.2 psi max cabin differential pressure NO Whichever occurs later: -Within 1,250 landings after September 6, 1983 (effective date of AD 83-15-08); or -Upon accumulation of 30,000 landings. Visual Inspection: -Every 1,250 landings Eddy Current Inspection: -Every 2,500 landings YES Visual Inspection: -Within 1,250 landings after the last visual inspection in accordance with AD 83-15-08. Eddy Current Inspection: -Within 2,500 landings after the last eddy current inspection in accordance with AD 83-15-08. Airplanes for which cabin max operating pressure is reduced to 6.0 PSI max cabin differential pressure NO or YES (as applicable) Visual Inspection: -The same as shown above for the max cabin differential pressure applicable to the airplane in question. Eddy Current Inspection: -Every 5,600 landings Eddy Current Inspection: -The same as shown above for the max cabin differential pressure applicable to the airplane in question. For all airplanes: Visual Inspection: -Every 1,875 landings
94-12-06: This amendment supersedes an existing airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A series helicopters, that currently requires repetitive inspections and replacement of certain lower belt drive pulley bearings (pulley bearings). This amendment retains the present AD requirements and adds an alternate pulley bearing to the requirements of the AD. This amendment is prompted by the introduction of an alternate pulley bearing into service by Schweizer Aircraft Corporation. The actions specified by this AD are intended to prevent failure of the pulley bearings, loss of power to the rotor systems, and subsequent loss of control of the helicopter.
2008-03-02: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 172R and 172S airplanes. This AD requires you to inspect the fuel return line assembly for chafing; replace the fuel return line assembly if chafing is found; and inspect the clearance between the fuel return line assembly and both the right steering tube assembly and the airplane structure, adjusting as necessary. This AD results from reports of chafed fuel return line assemblies, which were caused by the fuel return line assembly rubbing against the right steering tube assembly during full rudder pedal actuation. We are issuing this AD to detect and correct chafing of the fuel return line assembly, which could result in fuel leaking under the floor and fuel vapors entering the cabin. This condition could lead to fire under the floor or in the cabin area.
2000-03-20 R1: This amendment revises an existing airworthiness directive (AD), applicable to all Airbus Model A300 B4-601, B4-603, B4-620, B4-605R, B4-622R, and F4-605R (collectively called A300-600) series airplanes, that currently requires repetitive ultrasonic inspections to detect cracks on the forward fittings in the radius of frame 40 adjacent to the tension bolts in the center section of the wings, and various follow-on actions. That AD was prompted by reports of cracking due to fatigue-related stress in the radius of frame 40 adjacent to the tension bolts at the center/outer wing junction. The actions specified by that AD are intended to detect and correct fatigue cracking on the forward fittings in the radius of frame 40 adjacent to the tension bolts in the center section of the wings, which could result in reduced structural integrity of the wings. This amendment removes airplanes from the applicability of the existing AD. The incorporation by reference of certain publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of March 28, 2000 (65 FR 8642, February 22, 2000).
2020-05-25: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-200, -200PF, -200CB, and -300 series airplanes. This AD was prompted by a report that during a maintenance check an operator discovered cracking of the aft cargo compartment frames in the station 1460 frame web and inner chord between certain stringers. This AD requires an inspection of the fuselage frames for any existing repair, repetitive surface high frequency eddy current (HFEC) inspections of the fuselage frames with a cargo liner support channel for any cracking, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.