Results
99-19-22: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-19-22 which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GMBH (ECD) Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 helicopters by individual letters. This AD requires, before further flight, creating a component log card or equivalent record and determining the age and number of flights on each tension-torsion (TT) strap. The AD also requires inspecting and removing, as necessary, certain unairworthy TT straps. This amendment is prompted by an accident in which a main rotor blade (blade) separated from an ECD Model MBB-BK 117 helicopter because of fatigue failure of the TT strap. The ECD Model MBB-BK 117 and the BO-105 helicopters use the same part-numbered TT strap. The actions specified by this AD are intended to prevent failure of a TT strap, lossof a blade, and subsequent loss of control of the helicopter.
2013-08-15: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-800 series airplanes. This AD was prompted by reports of early fatigue cracks at chem-mill areas on the crown skin panels. This AD requires repetitive inspections for cracking of the fuselage skin along chem-mill steps at certain crown skin and shear wrinkle areas, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the skin panel at the specified chem-mill step locations, which could result in rapid decompression of the airplane.
96-18-17: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Garrett) TSCP700-4B, -4E, and -5 auxiliary power units (APUs), that requires removal from service of certain high pressure turbine (HPT) disks identified by serial number, and replacement with serviceable parts. This amendment is prompted by the discovery of a material defect in certain HPT disk forgings that may result in HPT disk rupture prior to reaching the disk cyclic life limit. The actions specified by this AD are intended to prevent an HPT disk rupture.
70-06-02: 70-06-02 BELL: Amdt. 39-955. Applies to all Model 204B 205A and 205A-1 helicopters and to any other helicopter incorporating tail rotor hub assembly, P/N 204-011-801-5 or -7 or P/N 204-011-701-11, -13 or -19 and to all spare tail rotor hub assemblies P/N 205-011-801-5 or -7 or P/N 204-011-701-11, -13 or -19. Compliance required as indicated. To prevent failure of the grip assemblies, P/N 204-011-728 or P/N 204-011-706, accomplish the following one time inspection on all tail rotor grip assemblies for proper hardness or conductivity before further flight, unless already accomplished after February 27, 1970. These inspections may be conducted with the grips installed on the helicopter. Determine the hardness of the grip assembly using a Rockwell Hardness or Eddy Current Tester, a Magnatest FM-120 (Magnaflux Corp.) or equivalent. Readings should be taken adjacent to vibro etched serial number between the blade retention bolts on grip face. Inspect all spare grip assemblies before installation. Remove grip assemblies with readings below Rockwell 79 on the "B" scale or above conductivity of 39 on International Annealed Copper Standard. This supersedes Amendment 39-953 (AD 70-06-01) issued by telegram dated February 27, 1970. This amendment is effective March 13, 1970, and was effective for all recipients of the telegram dated March 4, 1970 which contained this amendment.
2004-18-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 airplanes, that requires inspection of the fitting assemblies located on the vent and scavenge lines routed immediately below the fuel tank access covers on both wings for proper installation, and corrective actions if necessary. This amendment also requires inspection of the stiffeners on the underside of fuel tank access covers on both wings for signs of chafing damage caused by incorrect orientation of the lockwire tail, and removal of damage. This action is necessary to prevent contact between the lockwire pigtail of the fitting and the stiffener located on the inside surface of the fuel access covers of the wings, which could serve as a potential ignition source within the fuel tank if a cover is struck by lightning and result in possible fuel tank explosion. This action is intended to address the identified unsafe condition.
2022-13-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of the loss of all air data system information provided to the flightcrew during flight; the air data system information was recovered as the airplane descended to lower altitudes. This AD requires revising the existing airplane flight manual (AFM) to update the Unreliable Airspeed and Landing Distance Factor emergency procedures, which provide instructions for the flightcrew to stabilize the airspeed and altitude. The FAA is issuing this AD to address the unsafe condition on these products.
96-19-07: 96-19-07 BURKHART GROB LUFT-UND RAUMFAHRT: Priority Letter issued on September 6, 1996. Docket No. 96-CE-50-AD. Applicability: Models G115C, G115C2, G115D, and G115D2 airplanes (all serial numbers), certificated in any category. NOTE 1: This AD applies to each airplane 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 airplanes 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 (f) 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 prior to further flight after receipt of this priority letter AD, unless already accomplished. To prevent loss of control of the airplane caused by excessive speed or aerobatic maneuvers, accomplish the following: (a) Install, on the limitation placard at the left-hand cabin wall, the airspeed placard that is included with Grob Service Bulletin (SB) 1078-59/2, dated September 2, 1996. This placard reduces the maximum airspeed to 296 kilometers per hour (km/h); equal to 160 knots per hour. (b) Modify the airspeed indicator glass by accomplishing the following: (1) Place a red radial line on the indicator glass at 296 km/h (160 knots). The minimum dimensions for this radial line are 0.05 inches wide and 0.30 inches in length. (2) Place a white 0.05 inch minimum width slippage index mark connecting both the instrument glass and bezel. Locate this slippage index mark so that it does not obscure any airspeed markings. (c) Install, near the airspeed indicator,the red placard included with Grob SB 1078-59/2 that has the words: "Aerobatic maneuvers are prohibited." (d) Insert a copy of this AD into the Limitations Section of the airplane flight manual. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Division, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Division. NOTE 2: Information concerning the existence of approved alternative methodsof compliance with this AD, if any, may be obtained from the Brussels Aircraft Certification Division. (g) The service information and placards specified in this priority letter may be obtained from Burkhart Grob Luft-und Raumfahrt, D-8939 Mattsies, Germany. This information may also be examined at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (h) Priority Letter AD 96-19-07, issued September 6, 1996, becomes effective immediately upon receipt.
96-19-17: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757 series airplanes. This action requires a one-time inspection to detect discrepancies of the main battery shunt, and replacement with a serviceable part, if necessary. This action also requires inspection of certain wires, washers, and brass jam nuts to detect any discrepancy, and replacement with a serviceable part, if necessary. Additionally, this action requires inspection, and adjustment if necessary, of the torque and resistance of the installation of the main battery ground stud. This amendment is prompted by a report of interruption of electrical power during flight due to improper installation of the main battery shunt and ground stud connection of the main battery. The actions specified in this AD are intended to prevent such electrical power interruptions, which could result in loss of battery power to the source of standby power for the airplane.
2004-18-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-311 airplanes. This AD requires reviewing the airplane maintenance records to determine if you did the most recent bonding integrity inspection according to a certain revision of the Maintenance Program Support Manual (PSM), and doing related investigative and corrective actions if necessary. This AD is prompted by the discovery that a certain revision of the PSM omits several fuselage skin panels from a list of skin panels that must be inspected. We are issuing this AD to prevent disbonding of the subject skin panels, which could reduce the load-carrying capacity of the skin panels and result in reduced structural integrity of the airplane.
2022-13-08: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports of nose wheel steering (NWS) hydraulic motors jamming during pushback or towing. This AD requires doing an inspection to determine the part number and serial number of the NWS hydraulic motor, and re-identifying or replacing the NWS hydraulic motor if necessary. This AD also prohibits the installation of certain NWS hydraulic motors. The FAA is issuing this AD to address the unsafe condition on these products.
68-06-05: 68-06-05 FAIRCHILD-HILLER: Amdt. 39-565. Applies to FH-1100 type helicopters serial numbers 10 thru 76 inclusive and 83. Compliance required as indicated unless already accomplished. To preclude the possibility of failure of the engine-to-transmission coupling shaft due to corrosion resulting from water contamination, accomplish the following: (a) Within the next 100 helicopter hours' time in service following the effective date of this AD, remove Bendix coupling shaft P/N 19E49-3A and inspect for any corrosion and if found, replace with P/N 19E49-3B or if corrosion is absent modify in accordance with accomplishment instructions contained in Fairchild Hiller Service Bulletin No. FH-1100-24-1 dated January 25, 1968, or later FAA approved revision, or an equivalent inspection procedure or modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request, with substantiating data submitted through an FAA maintenance inspector, the compliance time may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective March 23, 1968.
2022-14-02: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A (LEAP-1A) model turbofan engines. This AD was prompted by a manufacturer investigation that revealed that certain high-pressure turbine (HPT) rotor stage 1 disks (HPT stage 1 disks) and a stages 6-10 compressor rotor spool were manufactured from material suspected to contain iron inclusion. This AD requires the replacement of certain HPT stage 1 disks and a stages 6-10 compressor rotor spool. The FAA is issuing this AD to address the unsafe condition on these products.
2004-18-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, 737-700, 737-700C, 737-800, and 737-900 series airplanes, that requires measuring the electrical resistance of the support bracket for the fire extinguisher bottle located in the left main landing gear wheel well to ensure that it does not exceed the maximum allowed resistance; and corrective actions, if necessary. This action is necessary to prevent high electrical resistance in the squib firing circuit, which could result in insufficient electrical current to fire the fire extinguisher bottle squib and discharge the fire extinguishing agent, which could lead to an uncontrolled engine fire. This action is intended to address the identified unsafe condition.
2022-13-19: The FAA is superseding Airworthiness Directive (AD) 2022-11- 03, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2022-11-03 required revising the existing airplane flight manual (AFM), and revising the operator's existing FAA-approved minimum equipment list (MEL) by incorporating certain master minimum equipment list (MMEL) provisions, to include limitations and procedures to mitigate the risk of elevator failure during flare. Since the FAA issued AD 2022-11-03, an updated software standard for the PRIMary flight control computers (PRIMs) has been developed to address the unsafe condition. This AD continues to require the actions in AD 2022- 11-03, and also requires installing an updated PRIM software standard, 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.
2013-08-23: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes. This \n\n((Page 24038)) \n\nAD was prompted by fuel system reviews conducted by the manufacturer. This AD requires adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2001-14-08 R1: The FAA is rescinding an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model DC-10 series airplanes, Model MD-10 series airplanes, and Model MD-11 series airplanes. That AD requires repetitive inspections of the numbers 1 and 2 electric motors of the auxiliary hydraulic pump for electrical resistance, continuity, mechanical rotation, and associated wiring resistance/voltage; and corrective actions, if necessary. We issued that AD to prevent various failures of electric motors of the auxiliary hydraulic pump and associated wiring, which could result in fire at the auxiliary hydraulic pump and consequent damage to the adjacent electrical equipment and/or structure. Since we issued that AD, we have determined that the inspection requirements are identical to the inspection requirements of another existing AD.
99-20-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspections of the lower engine mount to determine if the tangential link upper bolt and nut are oriented properly, and if the tangential link upper bolt nut is torqued within certain limits. Additionally, that amendment requires replacement of the bolt and nut with serviceable parts, if necessary, and requires certain follow-on actions for airplanes on which the upper bolt is missing. This amendment requires accomplishment of a previously optional terminating action or a new alternative terminating action for the repetitive inspections. This amendment is prompted by development of a new terminating action by the manufacturer. The actions specified by this AD are intended to prevent separation of the engine from the airplane due to migration of the tangential link upper bolt.
72-14-04: 72-14-04 NORTH AMERICAN ROCKWELL: Amdt. 39-1481. Applies to Models NA-265, NA-265-20, NA-265-30, NA-265-40 (Serial Nos. 282-1 thru 282-105), and NA-265-60 (Serial Nos. 306-1 thru 306-63). Compliance required as indicated: To prevent failure of the main landing gear wheel door torque tube assembly, P/N 265- 333338-1, -2, 285-333338-1, -2, -31, -32, as applicable, accomplish the following: (a) Within 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service, and at intervals not to exceed 100 hours' time in service thereafter, perform a dye penetrant inspection of the main landing gear wheel door torque tube in the area 3 inches adjacent to the fore and aft weldments for evidence of cracking, until (c), below, is accomplished. (b) If evidence of cracking is discovered as a result of any of the inspections of (a), above, replace the torque tube assembly with a new or serviceable assembly prior to further flight. Mark the rejected part to prevent inadvertent return to service (Note: The manufacturer has recommended that operators return parts for rework by them. If returned, and after rework, the mark may be removed, the part re-identified, and returned to service). (c) Replace main landing gear wheel door torque tube assemblies P/N 265-333338- 1, -2, 285-333338-1, -2, -31, -32 with torque tube assemblies P/N 285-333338-51, -52, 276- 933338-1, -2, -31, -32, -41, -42, -51, -52 as applicable. This amendment becomes effective July 7, 1972.
2022-13-07: The FAA is adopting a new airworthiness directive (AD) for all AutoGyro Certification Limited (type certificate previously held by RotorSport UK Ltd) Model Calidus, Cavalon, and MTOsport 2017 gyroplanes. This AD was prompted by reports of rotor blade longitudinal cracking and rotor blade attachment bolt hole fretting corrosion and cracking. This AD requires reducing the life limits for the rotor systems, repetitively inspecting each rotor blade, and depending on the outcome, removing parts from service. The FAA is issuing this AD to address the unsafe condition on these products.
69-04-01: 69-04-01\tBOEING: Amdt. 39-723. Applies to Model 727 Series airplanes in which the battery switch is located within ten inches of the galley switch. \n\n\tCompliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tAs a result of FAA evaluations of the 727 electrical system sufficient cause has been found to prevent inadvertent operation of the battery switch located on the flight engineer's panel. Inadvertent operation of the battery switch during some operating conditions could result in loss of the standby electrical system. \n\n\tTo prevent inadvertent operation of the battery switch on the flight engineer's panel on those 727 Series airplanes in which the battery switch is located within ten inches of the galley switch, accomplish one of the following: \n\n\t(1)\tInstall a guard (Grimes P/N 11170-1 or equivalent MS type painted black) on the battery switch. The guard must be installed to force the switch to the "on" position and the guard should be mounted with the hinge down. \n\n\t(2)\tReplace the battery switch with a detent lock type switch, P/N MS 25125-E3 or an equivalent MS type, provided the galley switch is a toggle type switch. \n\n\t(3)\tPerform an equivalent installation approved by the Chief, Aircraft Engineering Division, FAA, Western Region. \n\n\tIn each of the above installations, install decals as necessary to retain "bat" and "on-off" switch function and switch position identification. \n\n\tBoeing Service Bulletin No. 24-44 is forthcoming to cover same subject. \n\n\tThis amendment becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated January 31, 1969.
99-20-03: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) PW2000 series turbofan engines, that requires initial and repetitive inspections of certain High Pressure Turbine (HPT) stage 1 and stage 2 disks utilizing an improved ultrasonic inspection method performed at an approved facility when the disk is exposed during a shop visit, and if a crack indicating a subsurface anomaly is found, removal from service and replacement with a serviceable part. This amendment is prompted by the results of a stage 1 HPT disk fracture investigation, which has identified a population of HPT stage 1 and 2 disks that may have subsurface anomalies formed during a forging process. The actions specified by this AD are intended to prevent HPT disk fracture, which could result in an uncontained engine failure, and damage to the aircraft.
2004-17-04: The FAA supersedes Airworthiness Directive (AD) 2001-26-25, which applies to all Grob-Werke Gmbh & Co KG (Grob) Models G102 CLUB ASTIR III, G102 CLUB ASTIR IIIb, and G102 STANDARD ASTIR III sailplanes. AD 2001-26-25 currently requires you to apply a red mark and install a placard on the airspeed indicator to restrict the Vne airspeed. This AD requires you to install additional mass balance in the elevator and ailerons and determine resultant empty weight and empty weight center of gravity; incorporate a revision in the sailplane maintenance manual; and remove the red mark and the red placard on the airspeed indicator (both required by AD 2001-26-25). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent elevator flutter, which could cause structural damage. Such damage could result in loss of control of the sailplane.
2022-12-12: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney Division (PW) PW4062 model turbofan engines. This AD was prompted by a report of a manufacturing quality escape due to insufficient cooling of the low-pressure turbine (LPT) stage 5 air seal resulting in a reduction of the low-cycle fatigue (LCF) life limit. This AD requires removal and replacement of the LPT stage 5 air seal with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
96-17-11: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT9D-7R4 series turbofan engines, that requires replacement of 3rd, 4th, and 5th stage low pressure turbine (LPT) vane retention bolts and nuts, the removal of the 5th stage vane configuration which includes an electro-discharge machined (EDM) slot and replacement with a cast slot configuration, and prohibits the use of uncured anti-gallant compound on vane retention hardware. This amendment is prompted by reports of LPT failures that resulted in uncontained engine failures. The actions specified by this AD are intended to prevent LPT vane failures, which can result in uncontained engine failure, fire, and possible damage to the aircraft.
99-19-39: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes, that requires removal of the insulation blankets surrounding the emergency overwing exit hatches. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the freezing of moisture entrapped in the fiberglass/foam insulation installed on the fuselage structure between the overwing exit door and the fuselage door frame and intercostal, which could interfere with the opening of the overwing emergency exit hatches during an emergency evacuation of the airplane.