Results
2016-23-01: We are superseding Airworthiness Directive (AD) 2010-04-03 for all Airbus Model A310 series airplanes. AD 2010-04-03 required accomplishing repetitive detailed inspections for cracking around the fastener holes in certain wing top skin panels between the front and rear spars on the left- and right-hand sides of the fuselage, and repair if necessary. This new AD continues to require the repetitive detailed inspections, and also requires supplemental repetitive ultrasonic inspections for cracking around the fastener holes in wing top skin panels 1 and 2 at ribs 2 and 3, and repair if necessary. This AD was prompted by development of an ultrasonic inspection program to allow for earlier crack detection and extended repetitive inspection intervals. We are issuing this AD to detect and correct fatigue cracking around the fastener holes, which could result in reduced structural integrity of the airplane.
96-09-24: This amendment adopts a new airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2016-22-09: We are superseding Airworthiness Directive (AD) 2006-20-11 for certain The Boeing Company Model 757-200, -200CB, and -200PF series airplanes. AD 2006-20-11 required initial and repetitive detailed or high frequency eddy current (HFEC) inspections for cracks around the rivets at the upper fastener row of the skin lap splice of the fuselage, and repair of any crack found. This new AD no longer allows the detailed inspections and instead requires repetitive external HFEC inspections for cracking of the skin lap splices of the fuselage, and repair if necessary. This AD was prompted by an evaluation done by the design approval holder (DAH) indicating that the fuselage skin lap splice is subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking at certain skin lap splice locations of the fuselage, which could result in reduced structural integrity and rapid decompression of the airplane.
67-25-02 R3: 67-25-02 R3 BRITISH AEROSPACE: Amendment 39-477 as amended by Amendments 39- 485 and Amendment 39-909 is further amended by Amendment 39-5059. Applies to BAC 1-11 200 and 400 series airplanes, certificated in all categories. Compliance required as indicated unless previously accomplished. To prevent serious deterioration and failure of the flap drive screwjacks, accomplish the following: A. Perform a visual inspection of the flap drive screwjacks for evidence of unusual wear in accordance with paragraph 2.1.1 of British Aerospace BAC 1-11 Alert Service Bulletin 27-A-PM2992, Issue 4, dated November 30, 1979, prior to the accumulation of 750 landings or 800 hours time in service from the last inspection, whichever occurs earlier. Repeat the inspection at intervals not to exceed 800 hours time in service thereafter. B. Measure the nut-to-screw backlash in accordance with paragraph 2.2 of the service bulletin prior to the accumulation of 3,000 landings or 4,800 hours time inservice from the last check, whichever occurs earlier, and thereafter at intervals not to exceed 4800 hours time in service or 3000 landings, whichever occurs first. If the nut-to-screw backlash exceeds 0.03- inch, the screwjack assembly must be replaced with serviceable parts. C. Incorporation of modification PM2992, which introduces a new seal for the ball nut, constitutes terminating action for this AD. D. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. 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 inspections and/or modifications required by this AD. F. Upon request of an operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the inspection times specified in this AD to permit compliance at an established inspection period of that operator, if the request contains substantiating data to justify the increase for that operator. Amendment 39-477 became effective September 9, 1967. Amendment 39-485 became effective September 20, 1967. Amendment 39-909 became effective January 11, 1970. This Amendment 39-5059 becomes effective June 17, 1985.
2016-22-05: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney (PW) PW4164, PW4164-1D, PW4168, PW4168-1D, PW4168A, PW4168A-1D, and PW4170 turbofan engines. This AD was prompted by several instances of fuel leaks on PW engines installed with the Talon IIB combustion chamber configuration. This AD requires initial and repetitive inspections of the affected fuel nozzles and their replacement with parts eligible for installation. We are issuing this AD to prevent failure of the fuel nozzles, which could lead to engine fire and damage to the airplane.
2004-09-33: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 and 747-400D series airplanes, that requires a detailed inspection of the fire extinguishing system tube and clamp for correct installation or a repetitive pressure test of the fire extinguishing system tube for leakage, and corrective action, if necessary. This action is necessary to prevent a chafed hole in the fire extinguishing system tube of the aft cargo compartment, which could result in a lack of fire extinguishing agent and consequent uncontained fire in the aft cargo compartment. This action is intended to address the identified unsafe condition.
2016-22-11: We are superseding airworthiness directive (AD) 2013-02-06 for all Engine Alliance (EA) GP7270 and GP7277 turbofan engines with certain part number (P/N) high-pressure turbine (HPT) stage 2 nozzle segments installed. AD 2013-02-06 required initial and repetitive borescope inspections (BSI) and removal from service of these nozzles before further flight if one or more burn holes were detected in any HPT stage 2 nozzle segment. AD 2013-02-06 also required removal from service of these HPT stage 2 nozzle segments at the next engine shop visit. This AD requires the same inspections as AD-2013-02-06, requires removal of affected HPT stage 2 nozzles at next piece-part exposure, and adds certain P/Ns to the applicability. This AD was prompted by another report of inadequate cooling of the HPT stage 1 shroud and stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn- through of the turbine case, and in-flight shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure, uncontrolled fire, in- flight shutdown, and damage to the airplane.
51-22-01: 51-22-01 SIKORSKY: Applies to All Model S-51 Helicopters. Compliance required within the next 25 hours of operation, but not later than November 1, 1951. Due to the reported failures of Gear Shaft (Generator Drive-Tail Drive Transmission System) P/N S-10-35-1004, all shafts in service shall be replaced by shafts which have been jig drilled (i.e., the taper pin hole is located squarely with respect to the splines) and which have been stoned and polished to deburr and remove any sharp radii where the taper pin hole intersects the splines. (Sikorsky Service Information Circular No. 172, dated August 30, 1951, covers this same subject.)
2004-09-38: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-300 series airplanes, that requires various one-time inspections for discrepancies of the ground spoiler assemblies and the flap of each wing, and related investigative and corrective actions. This action is necessary to prevent failure of certain ground spoiler support arms due to interference between the ground spoiler assemblies and the wing flaps, which could result in loss of function of affected ground spoiler assemblies and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2016-22-02: We are adopting a new airworthiness directive (AD) for Embraer S.A. Models EMB-500 and EMB-505 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 incorrect installation of passenger seat attachment fittings. We are issuing this AD to correct the unsafe condition on these products.