Results
88-24-12: 88-24-12 BOEING: Amendment 39-6068. Applies to all Model 727 series airplanes, prior to line number 1620, not equipped with the safety bar modification described in Boeing Service Bulletin 727-32-275, Revision 2, dated March 30, 1984, certificated in any category. Compliance required within the next 3,500 flight cycles after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent failure of the main landing gear (MLG) to extend as a result of loosening of the self-locking nut at the attachment of the downlock forward pushrod assembly to the downlock torque shaft, accomplish the following: \n\n\tA.\tModify airplanes listed in Boeing Service Bulletin 727-32-0237, Revision 5, dated July 7, 1988, by installing the bolt, washer, nut, and cotter pin called out in item 5 of Figure 5 of that service bulletin. \n\n\tB.\tModify airplanes listed in Boeing Service Bulletin 727-32-0353, Revision 1, dated July 7, 1988, by installing the bolt, washer, nut, and cotter pin in accordance with that service bulletin. \n\n\tC.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment, 39-6068, becomes effective December 23, 1988.
97-02-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that requires modification of the system that detects a loss of tension in the cable controlling the flaps by removing the shim from behind the proximity switch and by trimming the switch bracket. This amendment is prompted by reports that the switch bracket can impair the movement of a pulley arm mechanism, ultimately preventing the detection system from operating. The actions specified by this AD are intended to prevent such impairment, which could result in movement of the flaps without action by the pilot, and ultimately cause reduced controllability of the airplane.
2004-26-03: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211-535E4-37, RB211-535E4-B-37, RB211-535C-37, RB211-535E4-B-75, and RB211-22B-02 turbofan engines. That AD currently requires inspecting certain high pressure (HP) turbine discs, manufactured between 1989 and 1999, for cracks in the rim cooling air holes, and, if necessary, replacing the disc's serviceable parts. This AD requires the same actions but at reduced compliance schedules and adds the RR model RB211-535E4-C turbofan engine to the applicability. This AD results from a report of cracks in a model RB211-524 HP turbine disc that had propagated further than expected. We are issuing this AD to prevent possible disc failure, which could result in an uncontained engine failure and damage to the airplane.
2023-10-01: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 190-300 and ERJ 190-400 airplanes. This AD was prompted by the excessive operation of certain elevator and rudder surfaces during manufacturing, causing damage and accelerating wear of internal parts of the power control units (PCUs). This AD requires replacement of the left-hand (LH) and right-hand (RH) elevator PCUs and lower and upper rudder PCUs, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
92-02-14 R1: The FAA is removing Airworthiness Directive (AD) 92-02-14, which applied to certain Airbus SAS Model A320 series airplanes. AD 92- 02-14 required inspection for correct installation of the flexible control cables on the overwing emergency escape slides. The FAA issued AD 92-02-14 to prevent failure of the overwing emergency escape slides to deploy, which would compromise use of the exit during an emergency. Since the FAA issued AD 92-02-14, no new occurrences of incorrect cable installations have been reported, and existing maintenance activities are adequate to prevent new occurrences. Therefore, the FAA has determined that AD 92-02-14 is no longer necessary. Accordingly, AD 92- 02-14 is removed.
2004-25-23: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that requires repetitive inspections for cracking of the top and side panel webs and panel stiffeners of the nose wheel well (NWW), and corrective actions if necessary. This action is necessary to detect and correct fatigue cracks in the top and side panel webs and stiffeners of the NWW, which could compromise the structural integrity of the NWW and could lead to the rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
2000-23-21: This amendment supersedes emergency airworthiness directive (AD) 2000-08-51. Emergency AD 2000-08-51 was sent to all known U.S. owners and operators of Teledyne Continental Motors (TCM) IO-360, TSIO-360, LTSIO-360, O-470, IO-470, TSIO-470, IO-520, TSIO-520, LTSIO-520, IO-550, TSIO-550, and TSIOL-550 series reciprocating engines by individual letters. This amendment requires removing a core sample of material from the propeller mounting flange of certain crankshafts, and sending the core sample to TCM for evaluation. This amendment is prompted by reports of crankshaft failures, and by the addition of additional crankshaft serial numbers (SN) that have been added to the suspect population. The actions specified by this AD are intended to prevent fracture of the crankshaft connecting rod journal, which could result in total engine power loss, in-flight engine failure and possible forced landing.
2009-07-01: We are adopting a new airworthiness directive (AD) for the products listed above. 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: It is necessary to change the limits of the High Pressure (HP) Turbine Stage 1 and Stage 2 Rotor Discs. The maximum approved life of these discs is decreased for all flight missions. This Emergency Airworthiness Directive (EAD) has been raised to instruct mandatory decreased maximum approved lives in the BR715 Time Limits Manual (TLM) T-715-3BR for the HP Turbine Stage 1 Rotor Disc for both Part No. BRH20130 and Part No. BRH20131 and of the High Pressure (HP) Turbine Stage 2 Rotor Disc for both Part No. BRH19423 and Part No. BRH19427 for all flight missions. The life limits are decreased by the same proportion for all flight missions, thus back to birth pro-rata calculations due to the life limit changes are not necessary. We are issuing this AD to prevent rotating parts that may have exceeded their low-cycle fatigue life limits from failing, which could result in uncontained engine failure and subsequent damage to the airplane.
2004-25-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Model EMB-135 and -145 series airplanes. This AD requires modification of the pitch trim system, which includes replacing certain components of the system with new or serviceable components, and upgrading certain software to a newer version. This action is necessary to prevent the temporary loss of the pitch trim command, which could result in reduced controllability of the airplane and consequent injury to the flightcrew and passengers. This action is intended to address the identified unsafe condition.
88-06-04: 88-06-04 BOEING: Amendment 39-5872. Applies to Model 757 series airplanes listed in Boeing Service Bulletin 757-53-0038, dated August 27, 1987, certificated in any category. Compliance required within 18 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent structural failure of the vertical fin and horizontal stabilizers in the event of a failure of the aft pressure bulkhead, accomplish the following: \n\n\tA.\tInstall a vertical fin access door and horizontal stabilizer covers in accordance with Boeing Service Bulletin 757-53-0038, dated August 27, 1987, or later FAA-approved revision. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective April 22, 1988.
2014-11-10: We are superseding Airworthiness Directive (AD) 2008-08-09 for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2008-08-09 required revising the airworthiness limitations (AWL) section of the Instructions for Continued Airworthiness by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units and corrective actions if necessary. This new AD requires replacing certain PFS units with new redesigned PFS units, which would terminate the repetitive functional tests; and both adding and removing certain airplanes from the applicability. This AD was prompted by reports that the shear pin in the input lever of several PFS units failed due to fatigue; and by the development of a re-designed PFS unit, which eliminates the need for repetitive functional tests. We are issuing this AD to prevent undetected failure of the shear pins of both PFS units simultaneously, which could result inloss of pitch feel forces and consequent reduced control of the airplane.
2023-11-03: The FAA is superseding Airworthiness Directive (AD) 2022-18- 03, which applied to certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. AD 2022-18-03 required incorporating temporary revisions into the airplane flight manual (AFM) and the quick reference handbook (QRH) that modify procedures for windshield heat operation until the affected windshield assemblies are replaced. This AD retains all actions required by AD 2022-18-03 and corrects typographical errors in certain document numbers specified in certain paragraphs of the regulatory information. The FAA is issuing this AD to address the unsafe condition on these products.
51-20-03: 51-20-03 HILLER: Applies to the following Aircraft: Model UH-12, Serial Numbers 105 to 135, Inclusive. (Incorporating the Collective Pitch Ballast System); Model UH-12A, Serial Numbers 136 to 176, Inclusive, and 178, 180 and 181. Compliance required as noted below. In order to preclude the possibility of protrusion of the bushings from the collective pitch ballast system bracket with resultant reduction of the pitch range of the main rotor blades and restricted controllability, the following should be accomplished: (a) As soon as possible but not later than September 1, 1951, and at each 25-hour inspection period thereafter, visually inspect the collective pitch ballast system bracket P/N 31125-1 for protrusion of either upper or lower bushing P/N 31120-1. Particular inspection should follow each application of grease to the bracket. (b) If the bushing(s) are found to be protruding, the assembly should be reworked by installing set screws in accordance with United Helicopters Mandatory Bulletin No. 19. (c) Inspection of the bracket as specified in part (a) may be discontinued after the rework described in part (b) has been accomplished. (Hiller Helicopters Mandatory Service Bulletin No. 19 covers this same subject.)
2023-08-05: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports of cracks found in the pivot bulkhead forward outer chord of a certain station. Analysis revealed higher bending stresses across the chord than originally assessed. This AD requires repetitive detailed and high frequency eddy current (HFEC) inspections of the pivot bulkhead forward outer chord of a certain station and longeron fitting for cracking and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2014-13-11: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. This AD was prompted by reports of scribe-line-related fatigue cracks on Model 727 airplanes, which are similar in design to Model 707 airplanes, and Model 720 and 720B series airplanes. This AD requires inspections for scribe lines in the skin lap joints, external approved repairs, external features, skin butt joints, and decals; and related investigative and corrective actions if necessary. This AD also requires surface finish restoration. We are issuing this AD to detect and correct scribe lines, which can develop into fatigue cracks in the skin and cause rapid decompression of the airplane.
2004-26-01: The FAA adopts a new airworthiness directive (AD) for all Eagle Aircraft (Malaysia) Sdn. Bhd. Model Eagle 150B airplanes. This AD requires you to inspect the port and starboard undercarriage attach bracket for unwelded areas and replace the attach bracket if unwelded areas are found. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Malaysia. We are issuing this AD to detect and correct inadequate welding of the undercarriage, which could result in cracks. This failure could lead to loss of control of the airplane.
2014-13-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of installation of incorrect wire support clamps within the bay area of the left and right environmental control systems (ECS) during production; the ECS bay area is a flammable fluid leakage zone. Use of incorrect wire support clamps that are not fully cushioned could allow electrical power wiring to come in contact with the exposed metal of the improper clamp, causing a short circuit \n\n((Page 41091)) \n\nand subsequent electrical arcing. This AD requires inspecting to identify the part number of the wire support clamp, and related investigative and corrective actions if necessary. We are issuing this AD to prevent electrical arcing and a potential ignition source, which, in combination with flammable fuel vapors, could result in a fuel tank explosion, and consequent loss of the airplane.
81-14-06: 81-14-06 CESSNA: Amendment 39-4158. Applies to Model 172RG (S/Ns 172RG0001 through 172RG0769) airplanes certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To ensure the integrity of the rudder trim/nose gear steering bungee, accomplish the following: A) Prior to further flight, install a locally fabricated placard in clear view of the pilot, using letters at least 3/32 inch high, which reads: "ELEVATOR MOVEMENT MAY BE LIMITED WHEN RIGHT RUDDER IS APPLIED. IF THIS CONDITION IS ENCOUNTERED, CENTER THE RUDDER PEDALS, LAND AS SOON AS PRACTICAL AND COMPLY WITH AD 81-14-06 PRIOR TO FURTHER FLIGHT." B) The fabrication and installation of the required placard of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person. That individual must make an entry in the airplane maintenance records showing compliance with paragraph A) of this AD. C) On airplanes with over 150 hours time-in-service on the effective date of this AD, within the next 50 hours time-in-service, replace Part Number 2467003-1 rudder trim/nose gear steering bungee with Part Number 2467003-6 rudder trim/nose gear steering bungee. D) On airplanes with less than 150 hours time-in-service on the effective date of this AD, replace Part Number 2467003-1 rudder trim/nose gear steering bungee with Part Number 2467003-6 rudder trim/nose gear steering bungee prior to the accumulation of 200 hours time-in- service. E) Compliance with Paragraphs C) or D), as appropriate, allows removal of the placard installed in Paragraph A). F) Record compliance with this AD by an appropriate entry in the airplane maintenance records. This should include those airplanes where the provisions of this AD have already been accomplished. NOTE: Cessna Single Engine Service Letter SE80-99, Rev. 1, dated June 8, 1981, pertains to this subject. This amendment becomes effective July 13, 1981.
2004-26-02: The FAA is adopting a new airworthiness directive (AD) for GE CF34-3A, CF34-3A2, CF34-1A, CF34-3A1, CF34-3B, and CF34-3B1 series turbofan engines. This AD requires removal from service of certain high pressure compressor (HPC) forward spools, at the first piece-part level exposure after 6,000 cycles since new (CSN); but not later than 20,000 CSN for CF34-3B engines, and not later than 22,000 CSN for CF34-3A, CF34-3A2, CF34-1A, CF34-3A1, and CF34-3B1 engines. This AD results from an updated low-cycle fatigue (LCF) analysis performed on certain HPC forward spools. We are issuing this AD to prevent LCF cracks and failure of the HPC forward spool, which could result in an uncontained engine failure and damage to the airplane.
2023-09-04: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes, and certain Model 737-8 and -9 airplanes. This AD was prompted by reports of uncommanded escape slide deployments in the passenger compartment, caused by too much tension in the inflation cable and the movement of the escape slide assembly in the escape slide compartment. This AD requires inspecting all escape slide assemblies to identify affected parts, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2023-09-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2000-08-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections or checks to detect broken H-11 steel bolts at the wing rear spar side-of-body on the lower chord splice plate and kick fitting; and corrective actions, if necessary. This AD also requires eventual replacement of the existing bolts with new Inconel bolts, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report of broken bolts at the wing rear spar side-of-body on the lower chord splice plate. The actions specified by this AD are intended to prevent cracking of the bolts due to stress corrosion, which could result in reduced structural integrity of the wing-to-body joint structure.
2000-08-16: This amendment adopts a new airworthiness directive (AD) that applies to Eurocopter Deutschland GMBH (ECD) Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters. This AD requires modifying the engine and transmission cowling doors (cowling doors). This amendment is prompted by an emergency landing of an ECD Model MBB-BK 117 helicopter after the No. 1 engine cowling opened, separated from the helicopter, and struck the main and tail rotor blades resulting in a tail rotor imbalance and subsequent departure of the tail rotor gear box from the helicopter. The actions specified by this AD are intended to prevent the cowling doors opening during flight, separating from the helicopter and impacting the main or tail rotor blades, and subsequent loss of control of the helicopter.
83-07-02: 83-07-02 WYTWORNIA SPRZETU KOMUNIKACYJNEGO, "PZL MIELEC": Amendment 39-4601. Applies to Model PZL M18 Serial Nos. 1Z003-01 through 1Z003-010, 1Z004-05 through 1Z004-010, 1Z005-01 through 1Z005-15 airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent flutter and buffeting which could cause structural damage to the airplane, accomplish the following: a) Within the next 50 hours time-in-service after the effective date of the AD, reinforce all counterweights (elevator and rudder) as prescribed in Mandatory Bulletin Nos. I/010/81 dated February 1981 and U/019/81 dated November 1981. b) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. c) An equivalent method of compliance with this AD if used must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. Thisamendment becomes effective on April 7, 1983.
2023-08-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters (Airbus) Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD is prompted by modifications developed by Airbus to address a report of an emergency exit window that required excessive pushing force to jettison. This AD requires removing skived polytetrafluoroethylene tape (PTFE tape) (if installed) and replacing certain polychloroprene seals with silicone seals, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits installing a jettisonable window unless the actions required by this AD have been accomplished. The FAA is issuing this AD to address the unsafe condition on these products.