Results
2007-03-16: 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 an excessive lateral play caused by a nonconforming washer that might lead to the deterioration of the elevator trim tab bearing fatigue resistance. We are issuing this AD to require actions to correct the unsafe condition on these products.
2007-03-14: 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: This AD is prompted by several reported cases of rupture of the (hydro-mechanical metering unit (HMU)) constant delta pressure valve diaphragm on Arriel 2B1 engines, due to the wear of the delta P diaphragm fabric. Rupture can result in the loss of the automatic control mode of the helicopter, accompanied with a deterioration of the behavior of the auxiliary back-up mode (emergency mode). The loss of automatic control mode coupled with the deteriorated performance of the backup mode can lead to the inability to continue safe flight, forced autorotation landing, or an accident. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
69-25-04: 69-25-04 FAIRCHILD-HILLER: Amdt. 39-886. Applies to Fairchild Hiller F-27 and FH-227 type Airplanes, except FH-227D and FH-227E, certificated in all categories. To prevent the hazards associated with the flaps driving off the ends of the screw jacks due to a single failure of the drive system which actuates the normal flap control limit switches and the emergency power cutoff switches, accomplish the following: (a) Within the next 100 hours' in service after the effective date of this airworthiness directive, unless already accomplished within the last 25 hours in service, and thereafter at intervals not to exceed 125 hours' in service, until incorporation of the modification noted in (b). (1) Inspect the universal joint at each end of the wing flap connecting shaft assembly P/N 27-727994-11 located between the flap motor gearbox at wing station 141 left (installed in the wheel well of the left nacelle) and the gearbox at wing station 121 left, to assure some freedom of movement in all axes. (2) Inspect the universal joint of the actuator shaft P/N 27-727920-7, -9, or -13, as applicable, also located on the gearbox at wing station 121 left, noted in (a)(1) above, to assure some freedom of movement in all axes. (3) If freedom of movement is not determinable, remove and replace deficient universal joint pin or bolt before further flight. (4) Lubricate the three universal joints, noted in (a)(1) and (a)(2) above, in accordance with applicable maintenance manual instructions. (b) Within the next 1000 hours' in service after the effective date of this airworthiness directive, unless already accomplished, separate the existing flap "up and down" limit switches from the emergency flap power cutoff switches by complying with Fairchild Hiller Service Bulletin F-27-27-64, Revision 3, dated 1 October 1969, for F-27 type airplanes with pre-select flap control, and Fairchild Hiller Service Bulletin FH-227-27-22, Revision 1, dated 2April 1969 for FH-227 type airplanes, or later revisions thereto, or equivalent modification both approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Upon request with substantiation data submitted through an FAA maintenance inspector, compliance time may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective December 6, 1969.
2007-03-07: The FAA is superseding an existing airworthiness directive (AD) that applies to all Boeing Model 737 airplanes. The existing AD currently requires installation of a new rudder control system and changes to the adjacent systems to accommodate that new rudder control system. For certain airplanes, this new AD adds, among other actions, repetitive tests of the force fight monitor of the main rudder power control unit (PCU), repetitive tests of the standby hydraulic actuation system, and corrective action; as applicable. For those airplanes, this new AD also adds, among other actions, replacement of both input control rods of the main rudder PCU and the input control rod of the standby rudder PCU with new input control rods, as applicable, which ends the repetitive tests. For certain other airplanes, this new AD adds installation of an enhanced rudder control system in accordance with new service information. This AD results from a report of a fractured rod end of an input controlrod of the main rudder PCU and a subsequent report of a fractured rod end of the input control rod of the standby rudder PCU. We are issuing this AD to prevent failure of one of the two input control rods of the main rudder PCU, which, under certain conditions, could result in reduced controllability of the airplane; and to prevent failure of any combination of two input control rods of the main rudder PCU and/or standby rudder PCU, which could cause an uncommanded rudder hardover event and result in loss of control of the airplane.
84-21-02: 84-21-02 BOEING: Amendment 39-4936. Applies to Boeing Model 747 series airplanes, certificated in all categories, listed in Section 3.0 of Boeing Document No. D6-35022, "Supplemental Structural Inspection Document" (SSID), Revision A, dated April 1984. Compliance is required as indicated in the body of the AD.\n\n\tTo ensure the continuing structural integrity of the total Boeing Model 747 fleet accomplish the following on the candidate fleet, unless already accomplished:\n\n\tA. Within one year after the effective date of the AD, incorporate a revision into the FAA approved maintenance inspection program which provides no less than the required Damage Tolerance Rating (DTR) for each Structural Significant Item (SSI) listed in Boeing Document D6-35022, Revision A, dated April 1984, or later FAA approved revisions. The required DTR value for each SSI is listed in the document. The revision to the maintenance program shall include and be implemented in accordance with the proceduresin Sections 5.0 and 6.0 of the SSID.\n\n\tB. Cracked structure must be repaired before further flight in accordance with an FAA approved method. \n\n\tC. Aircraft may be ferried to a maintenance base for repair in accordance with FAR 21.197 and 21.199.\n\n\tD. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tE. Operators who have acceptably incorporated Boeing Document No. D6-35022, Revision A, dated April 1984, or later FAA approved revisions, into their approved maintenance program are exempt from the provisions of this AD.\n\n\tNOTE: Acceptable incorporation is considered to include the reporting requirements of Section 6.0 of the SSID.\n\n\tAll persons affected by this directive who have not already received these 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 also be examined at FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington.\n\n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1).\n\n\tThis amendment becomes effective November 23, 1984.
2000-17-07: This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model EC120B helicopters. This action requires adjusting the clearance of the cabin sliding door if necessary. This amendment is prompted by an in-flight loss of a cabin sliding door, which had been locked in the fully opened position. The actions specified in this AD are intended to prevent in-flight loss of a cabin sliding door, impact with the horizontal stabilizer, main rotor, or fenestron tail rotor, and subsequent loss of control of the helicopter.
2018-25-04: We are adopting a new airworthiness directive (AD) for certain C Series Aircraft Limited Partnership (CSALP) Model BD-500-1A10 and BD- 500-1A11 airplanes. This AD was prompted by reports of dislodged cargo compartment blowout panels. This AD requires repetitive inspections for any dislodged blow-out panel in the forward and aft cargo compartments, reporting of the inspection findings, and reinstallation if necessary. We are issuing this AD to address the unsafe condition on these products.
2021-19-03: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by reports of spurious in-flight disconnections of the automatic flight control system (AFCS). This AD requires updating certain ''Primus Epic'' system software, as specified in a European Aviation Safety Agency (now 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.
2007-03-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as executive seats equipped with pedestal legs that were produced using a material that deviates from the approved design data. We are issuing this AD to require actions to correct the unsafe condition on these products.
2018-25-10: We are superseding Airworthiness Directive (AD) 2018-11-07, which applied to all Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. AD 2018-11-07 required a one-time inspection of an affected lug attaching the aileron bellcrank support bracket to the rear spar of the wing and the adjacent area of the installed support brackets, a thickness measurement of the affected lug, repetitive inspections of the affected aileron bellcrank support brackets, and corrective actions if necessary. AD 2018-11-07 also provided an optional terminating action for the repetitive inspections. This AD retains the actions of AD 2018-11-07 and requires the terminating action for the repetitive inspections. This AD was prompted by a determination that it is necessary to require the terminating action. We are issuing this AD to address the unsafe condition on these products.
2007-01-11: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Bombardier Model DHC-8-100, -200, and - 300 series airplanes. That AD currently requires modification of the flight compartment door; repetitive inspections for wear of the flight compartment door hinges following modification; and repair or replacement of the hinges with new hinges if necessary. This new AD requires using revised procedures for modifying and inspecting the flight compartment door and reduces the applicability of the existing AD. This AD results from a determination that certain cockpit doors are no longer subject to the existing requirements. We are issuing this AD to prevent failure of the alternate release mechanism of the flight compartment door, which could delay or impede the evacuation of the flightcrew during an emergency. This failure also could result in the flightcrew not being able to assist passengers in the event of an emergency. DATES: This AD becomeseffective March 5, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 5, 2007. On May 12, 1999 (64 FR 16803, April 7, 1999), the Director of the Federal Register approved the incorporation by reference of Bombardier Service Bulletin S.B. 8-52-39, Revision `C,' dated September 1, 1997; and Bombardier Service Bulletin S.B. 8-52-39, Revision `D,' dated February 27, 1998.
2007-02-17: 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: In operation, fuel leaks at the level of start electro valve fuel coupling were observed. A lack of power or an uncommanded in- flight shutdown may result from these fuel leaks. The condition described in the MCAI may result in a forced autorotation landing, the inability to continue safe flight, or a fire. We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-18-16: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited (Bell) Model 429 helicopters. This AD was prompted by reports of tail rotor gearbox assemblies found loose on the gearbox support. This AD requires repetitive torque checks of the tail rotor gearbox attachment hardware, and corrective action if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2018-23-16: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL 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 insufficient clearance between the pitot tubes and the primary support at the flame arrester intersection. We are issuing this AD to require actions to address the unsafe condition on these products.
2004-08-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-600 and A300 C4-600 series airplanes, that requires a one-time inspection to detect damage of the pump diffuser guide slots (bayonet) of the center tank fuel pumps, the pump diffuser housings, and the pump canisters; repetitive inspections to detect damage of the fuel pumps and the fuel pump canisters; and corrective action, if necessary. This action is necessary to detect and correct damage of the center tank fuel pumps and fuel pump canisters, which could result in separation of a pump from its electrical motor housing, loss of flame trap capability, and a possible fuel ignition source in the center fuel tank. This action is intended to address the identified unsafe condition.
98-13-37: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 and all Model A300-600 series airplanes, that requires a one-time inspection for cracking of the gantry lower flanges in the main landing gear (MLG) bay area; and repair, if necessary. 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 detect and correct cracking of the gantry lower flanges in the MLG bay area, which could result in decompression of the airplane.
2018-24-06: We are adopting a new airworthiness directive (AD) for Leonardo S.p.A. (Leonardo) Model AW189 helicopters. This AD requires replacing the tail plane lower fitting with an improved tail plane lower fitting. This AD was prompted by reports of cracks on the tail plane fittings of Model AW189 helicopters. The actions of this AD are intended to correct an unsafe condition on these products.
2018-20-03 R1: We are revising airworthiness directive (AD) 2018-20-03 for certain Hoffmann GmbH & Co. KG (Hoffmann) model HO-V 62 propellers. AD 2018-20-03 required removal of the affected propeller blades and installation of modified propeller blades marked with a change letter ``A'' or ``B'' suffix. This AD requires the removal and replacement of the affected propeller blades and installation of modified propeller blades marked with a change letter ``A'' or ``B'' suffix. This AD was prompted by a determination that the applicability and installation prohibition paragraphs of AD 2018-20-03 were incorrect. We inadvertently included all Hoffmann model HO-V 62 propeller blades that did not have a change letter ``A'' or ``B'' suffix added to the serial number (S/N) and marked on the blade in the applicability and installation prohibition paragraphs of AD 2018-20-03. Only Hoffmann model HO-V 62 propellers with certain S/Ns without a change letter ``A'' or ``B'' suffix are affected. We are issuing this AD to address the unsafe condition on these products.
80-26-05: 80-26-05 PIPER: Amendment 39-3994. Applies to Piper Models PA-31, PA-31-300, PA-31-325, Serial Nos. 31-2 thru 31-8012077; PA-31-350, Serial Nos. 31-5001 thru 31- 8052168; PA-31P, Serial Nos. 31P3 thru 31P-7730012; PA-31T1, Serial Nos. 31T-7804001 thru 31T-8004040; and PA-31T, Serial Nos. 31T-7400002 thru 31T-8020076 certificated in all categories. To prevent hazards associated with failed landing gear door attachments interfering with landing gear operation, accomplish the following: a. Within the next 100 hours in service from the effective date of this AD and thereafter at intervals not to exceed 100 hours in service from the last inspection, inspect the main landing gear inboard door hinges and hinge attachment angles in accordance with the "Instructions" section of Piper Service Bulletin No. 682 dated July 24, 1980, or equivalent. b. If cracks are observed, repair in accordance with the "Instructions" section of Piper Service Bulletin No. 682 dated July 24, 1980, or equivalent, prior to further flight, except the aircraft may be flown in accordance with FAR 21.197 to a base where a repair can be made. c. Upon the incorporation of, or the determination that the door hinges are P/N 47529-32, or are an equivalent part, the repetitive inspection of the hinges may be discontinued. Hinges manufactured by Piper from .250 sheet steel have been found to be equivalent to P/N 47529-32. d. Upon the incorporation of, or the determination that the hinge attachment angles are P/N 42048-02, -03 or are an equivalent part, the repetitive inspection of the angles may be discontinued. Four inch long angles manufactured by Piper have been found to be equivalent to P/N 42048-02, -03. e. Equivalent inspections, repairs and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. f. Upon the submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection interval specified in the AD. This amendment is effective December 19, 1980.
2007-02-16: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Saab Model SAAB-Fairchild SF340A and SAAB 340B airplanes. That AD currently requires repetitive inspections for wear of the brushes and leads and for loose rivets of the direct current (DC) starter generator, and related investigative/corrective actions if necessary. This new AD requires installing new, improved generator control units (GCUs). Installing the GCUs ends the repetitive inspection requirements of the existing AD. This AD results from reports of premature failures of the DC starter generator prior to scheduled overhaul. We are issuing this AD to prevent failure of the starter generator, which could cause a low voltage situation in flight and result in increased pilot workload and reduced redundancy of the electrical powered systems. DATES: This AD becomes effective March 1, 2007. The Director of the Federal Register approved the incorporation by reference of a certainpublication listed in the AD as of March 1, 2007. On April 1, 2005 (70 FR 9215, February 25, 2005), the Director of the Federal Register approved the incorporation by reference of Saab Service Bulletin 340-24-035, dated July 5, 2004, including Attachment 1 (Goodrich Service Information Letter 23080-03X-24-01), dated July 1, 2004.
2007-02-14: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires testing the electrical resistance of the bond between the bulkhead fitting for the fuel feed line and the front spar of the left and right wings, inspecting an adjacent bonding jumper to make sure it is installed correctly, and performing corrective and other specified actions as applicable. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent arcing or sparking in the fuel tank in the event of a lightning strike, which could result in an uncontrolled fire or explosion.
2018-23-10: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by leakage of shrouded pipe T-boxes in the potable water system. This AD requires replacement of the affected potable water T-boxes and clamps with new parts. We are issuing this AD to address the unsafe condition on these products.
2000-16-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 340B series airplanes. This action requires adjustment of the cargo baggage net, replacement of baggage net placards with new placards, and installation of certain new baggage net placards. This action is necessary to prevent failure of the cargo bulkhead floor attachments, which could result in damage to the airplane structure and possible injury to passengers and crewmembers. This action is intended to address the identified unsafe condition.
81-09-09: 81-09-09 STEWART-WARNER (SOUTH WIND DIVISION): Amendment 39-4102. Applies to Model Series 8240, 8253, 8259, and 8472 marked as meeting the standards of FAA TSO-C20, installed in aircraft certificated in all categories. Compliance required as indicated. To prevent a hazardous condition caused by deterioration of the combustion heater, accomplish the following: A. For combustion heaters having 250 hours or more time in service after the effective date of this AD, conduct the 250 hour inspection in accordance with the manufacturer's service manual (see Note 2) within the next 50 hours of combustion heater operation, unless already accomplished within the last 200 hours of heater time, and thereafter at intervals not to exceed 250 hours of combustion heater operation. Also, along with the above inspection, a general inspection of the combustion heater installation must also be accomplished including at least the following: 1. Inspect ventilating air and combustion airinlets and exhaust outlet correcting restrictions and insuring attachment security. 2. Inspect drain line and insure it is free of obstruction. 3. Check all fuel lines for security at joints and shrouds, correcting those showing evidence of looseness or leakage. 4. Check all electrical wiring for security at attachment points, correcting conditions leading to arcing, chafing or looseness. B. For combustion heaters having 1000 hours or more time in service after the effective date of this AD, overhaul the combustion heater in accordance with the manufacturer's service manual (See Note 2) within the next 50 hours of combustion heater operation, unless already accomplished within the last 950 hours of heater time, and thereafter at intervals not to exceed 1000 hours of combustion heater operation. An overhaul consists of complete disassembly, cleaning, repair, reassembly and test as outlined in the appropriate service manual. Note 1 - In complying with this AD, if the owner or operator cannot document combustion heater operative time, the aircraft time must be used. Note 2 - The following is a list of combustion heaters covered by this AD and the appropriate service manual. Methods of inspection or overhaul other than those contained in the manufacturer's service manuals must be approved by the Chief, Engineering and Manufacturing Branch, FAA Great Lakes Region. Models Service Manual Number 8240 Series 09-998 or P.M. 35710 8259 Series (Appropriate usage is shown in Manual or Manual Supplements) 8253 Series P.M. 20688 8472 Series 09-1015 This amendment becomes effective May 8, 1981.
2007-02-02: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 airplanes. This AD requires a one-time inspection for previous repairs of the aft fuselage skin panel at the longeron 28 skin splice; repetitive inspections for cracks of the same area; and related investigative and corrective actions. This AD also provides optional actions for extending the repetitive inspection intervals. The actions specified by this AD are intended to detect and correct cracks in the aft fuselage skin at the longeron 28 skin splice, which could lead to loss of structural integrity of the aft fuselage, resulting in rapid decompression of the airplane. This action is intended to address the identified unsafe condition.