Results
2008-03-14: 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: Due to pressurization loads, the fuselage frame of the emergency exit door could suffer from fatigue and develop cracks in its corners. The superseded Italian Airworthiness Directive (AD) 1995- 059 was issued to require modification of the emergency door frame in accordance with Piaggio (at the time I.A.M. Rinaldo Piaggio S.p.A.) Service Bulletin 80-0057 original issue. Parts necessary to carry out the modification were a new door pan assembly and a doubler; Since these parts are no longer available, Piaggio Aero Industries S.p.A. (PAI) designed new suitable part numbers introduced by Revision 1 of Service Bulletin 80-0057. The present AD mandates modification of the fuselage emergency door frame in accordance with Revision 1 of Service Bulletin 80-0057 from PAI. We are issuing this AD to require actions to correct the unsafe condition on these products.
94-18-06: This amendment adopts a new airworthiness directive (AD) that is applicable to Textron Lycoming LTS101 series turboshaft and LTP101 series turboprop engines. This action requires a one-time removal of 321 No. 2 bearings with serial numbers from suspect manufacturing lots, and replacement with serviceable parts. This amendment is prompted by reports of three in- service bearing failures. The actions specified in this AD are intended to prevent engine power loss and inflight engine shutdown due to No. 2 bearing failure, which could result in possible loss of the aircraft.
2001-14-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Cessna Model 560XL airplanes. This action requires inspection of certain electrical wiring of the landing light switch, associated components, and the aft J-box fairing light relay wire for chafing, discoloration, or damage; rerouting of certain wiring; and corrective follow-on actions, if necessary. This action is necessary to prevent shorting to the ground of the electrical power due to chafing of wiring, which could result in electrical fire in the wiring of the landing light switch, associated components, and the wiring of the aft J-box fairing light relays. This action is intended to address the identified unsafe condition.
78-10-04: 78-10-04 AIRESEARCH MANUFACTURING COMPANY OF ARIZONA: Amendment 39-3216. Applies to AiResearch Model TSCP700-4B and -5 Auxiliary Power Units (APU's) which have first stage compressor disks P/N's 969600-1 or -2 installed, of the serial numbers listed. Disk Serial No. 7-03501-2503 7-03501-2531 7-03501-2504 7-03501-2532 7-03501-2506 7-03501-2538 7-03501-2507 7-03501-2545 7-03501-2510 7-03501-2546 7-03501-2511 7-03501-2548 7-03501-2513 7-03501-2549 7-03501-2514 7-03501-2558 7-03501-2519 7-03501-2582 7-03501-2522 7-03501-2588 7-03501-2523 7-03501-2599 7-03501-2526 7-03501-2606 7-03501-2527 7-03501-2619 7-03501-2718 7-03501-2529 7-03501-2743 Compliance required before accumulating a total of more than 3000 cycles on the first stage compressor disks, or within the next 300 cycles after the effective date of this AD, whichever occurs later, unless already accomplished: To prevent a high energy release of first stage compressorblades and disk parts due to the possible fatigue failure of the disk, accomplish the following: (a) Remove the first stage disk from the compressor section of the APU and replace with like serviceable part. (b) For the purposes of this AD: (1) A cycle is defined as a start and acceleration to at least 95% high pressure spool (N2) rpm followed by a shutdown, during which low pressure spool (N1) rpm reaches, or exceeds, 97% rpm nominal. If, in any start, operating and shutdown sequence, the low pressure spool (N1) is prevented from exceeding 91% rpm nominal, only one half of a cycle must be recorded. (2) Operators who have not kept a record of operating starts on individual disks may assume two starts have occurred for each recorded APU operating hour of service, or any other cycle per hour ratio approved by the operators' assigned FAA maintenance inspector, provided the request contains substantiating data to justify the alternative ratio. (3) Operators whohave not kept a record of APU operating hours of service shall estimate hours of APU operation equating APU operation to airplane hours time in service using a ratio approved by the operator's assigned FAA maintenance inspector and justified by substantiating data. NOTE: AiResearch Service Bulletin TSCP700-49-5016 dated April 25, 1978 refers to the same subject. This amendment becomes effective May 30, 1978.
2018-17-07: We are superseding Airworthiness Directive (AD) 2017-24-01, which applied to certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 airplanes and Model ATR72-212A airplanes. AD 2017-24-01 required an inspection for routing attachments of electrical harness bundles and for wire damage, and corrective actions if necessary. This new AD adds additional airplanes to the applicability. This AD was prompted by a determination that additional airplanes are affected by the unsafe condition. We are issuing this AD to address the unsafe condition on these products. [[Page 40964]]
2001-13-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-700 and -800 series airplanes, that requires inspections of certain tension bolts at the attachment of the aft pressure bulkhead to the fuselage at body station 1016 to determine if the correct parts are installed, and corrective action, if necessary. The actions specified by this AD are intended to prevent fatigue cracking along the bulkhead-to-fuselage attachment, which could result in structural failure of the aft pressure bulkhead and consequent rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
2018-16-01: We are adopting a new airworthiness directive (AD) for certain B/E Aerospace Fischer GmbH Attendant Seats NG and Pilot Seats 120/335. This AD requires removing and replacing the energy absorber (EA) assemblies on affected pilot seats and the removing and replacing affected attendant seats. This AD was prompted by the discovery that rivets with insufficient strength were used during the manufacture of EA assemblies installed on certain seats. We are issuing this AD to address the unsafe condition on these products.
2001-13-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, and -301 series airplanes, that requires repair of the flight deck angle. The actions specified by this AD are intended to prevent the flight deck angle from interfering with the clevis of the roll control disconnect cable, which could lead to an uncommanded disconnection of the roll control, resulting in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2018-17-05: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports that electro-hydrostatic actuators (EHAs), installed on the inboard ailerons, elevators, and rudder, had degraded insulation resistance in the direct drive solenoid valve (DDSOV), due to incorrect sealing application. This AD requires a check of the insulation resistance of the DDSOV of each affected EHA and applicable corrective actions. We are issuing this AD to address the unsafe condition on these products.
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.