Results
2016-04-13: We are superseding airworthiness directive (AD) 2015-04-03 that applies to certain Rolls-Royce plc (RR) RB211 Trent 768-60, 772- 60, and 772B-60 turbofan engines. AD 2015-04-03 required inspection of the sealing sleeve on the high-pressure/intermediate-pressure (HP/IP) turbine support internal oil feed tube and removal of those sealing sleeves affected by AD 2015-04-03. This AD requires removal of either the affected sealing sleeve only or both the affected sealing sleeve and the oil feed tube. This AD was prompted by fractures of the HP/IP turbine support internal oil feed tube. We are issuing this AD to prevent failure of the HP/IP turbine support internal oil feed tube, uncontained engine failure, and damage to the airplane.
2010-21-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Within the framework of the A300-600 aircraft Service Life Extension programme (42,500 FC [flight cycles]), it has been concluded that a reinforcement of the junction of frame bases at FR48, FR49 and FR51 to FR53 is necessary to enable the aircraft to reach the Extended Service Goal (ESG). * * * [Failure of the frame base], if not corrected, could affect the structural integrity of the fuselage. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2016-05-04: We are adopting a new airworthiness directive (AD) for certain Dowty Propellers R352/6-123-F/1, R352/6-123-F/2, and R410/6-123-F/35 model propellers. This AD was prompted by reports of dowel hole cracks in the face of the rear hub half. This AD requires installing dowel hole liners as necessary. We are issuing this AD to prevent loss of structural integrity of the propeller hub, which could result in damage to the propeller and damage to the airplane.
2001-23-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires a one-time review of records to determine whether an airplane has been repainted since its delivery from the factory; and a one-time inspection to detect damage associated with improper preparation for the repainting, and corrective action if necessary. This amendment is prompted by mandatory continuing airworthiness information from a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct damage to the aluminum skin of the airplane, which could result in a weakening of the structure of the airplane.
2016-05-11: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires certain inspections of the main rotor and tail rotor control pushrods (pushrods). This AD is prompted by a Sikorsky investigation that indicated that some pushrods may have incorrectly installed locking mechanisms. These AD actions are intended to detect an incorrectly installed locking mechanism, which if not corrected, could result in a loose jam nut, failure of the pushrod, loss of main rotor or tail rotor flight control, and consequent loss of helicopter control.
2015-12-12: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by a report of two cases of heavy (hard to move) aileron control caused by aileron cables stuck in a clump of ice in the wheel bay. This AD requires installing drain tubes on the center wing rear spar. We are issuing this AD to prevent accumulated water near or on the aileron control cables, which could freeze and result in reduced control of the airplane.
2005-12-13: The FAA is adopting a new airworthiness directive (AD) to supersede AD 2005-05-52 (70 FR 13362, March 21, 2005), which applies to all Cessna Aircraft Company (Cessna) Models 402C and 414A airplanes. AD 2005-05-52 currently requires you to eddy current inspect the forward wing spars and visually inspect the aft and auxiliary spars. This AD is the result of fatigue and crack growth analyses of the wings of these airplanes, recent cracks found on Model 402C airplanes, and the FAA's determination that repetitive inspections and a wing spar modification are necessary to address the unsafe condition. Consequently, this AD would require repetitive eddy current inspections, visual inspections, and a spar strap modification on each wing. You must retain the actions of AD 2005-05-52 until you do the modifications of this AD. The actions specified by this AD are intended to prevent wing spar cap failure caused by undetected fatigue cracks. Such failure could result in loss of a wing withconsequent loss of airplane control. FAA is also issuing AD 2005-12-12 to require the spar strap modification and long-term inspections on Models 401, 401A, 402, 402A, 402B, 411, and 411A airplanes.
53-15-03: 53-15-03 HARTZELL: Applies to All Model HC-82XF-1 Controllable Pitch Propellers Installed on Cessna 180 Aircraft. Compliance required as indicated. A number of recent in service failures of the pitch change link screws (P/N A-98) on Hartzell HC-32XF-1 propellers have resulted in exposing the occupants to hazardous situations. All such propeller failures have resulted in forced landings, some of which caused major damage to the aircraft. Due to the serious nature of these failures, the following inspections and replacements are necessary: I. Inspection. A. Prior to August 1, 1953, visually inspect all link screws to determine: (1) If any are broken. (2) If any are cracked or bent. (3) If any are not fully seated on the conical seat. B. If any are found broken, cracked, bent or not fully seated on the conical seat, prior to further flight replace with screws as noted in item II. C. If visual inspection proves satisfactory, the propellermay be flown subject to compliance with item II. II. Replacement. Compliance required prior to September 1, 1953. A. Replace all original A-98 link screws with improved A-98-B link screws in accordance with Hartzell Service Bulletin No. 24, dated May 28, 1953. B. Propeller with serial numbers not listed in Service Bulletin No. 24 may not have the improved screws. Owners of these propellers shall check with the propeller manufacturer for verification.
64-02-01: 64-02-01 AERO COMMANDER: Amdt. 676 Part 507 Federal Register January 21, 1964. Applies to Models 500A, 500B, 560F, 680F (Pressurized) and 680FL Aircraft Serial Numbers 871, 875, and 893 through 1329 Except Serial Numbers 916, 953, 1162, 1186, 1207, 1224, 1234, 1293, 1303, 1325, 1327, and 1328. Compliance required as indicated. To detect loosened set screws and to preclude rotation of the upper retaining bearing on the main landing gear accomplish the following: (a) Within 25 hours' time in service after the effective date of this AD, inspect the main landing gear in accordance with Part I of Aero Commander Service Bulletin No. 83 dated September 13, 1963, or FAA approved equivalent. If the extension of either gear exceeds 9.125 plus or minus 0.125 inches, accomplish the modification specified in (b) for both main landing gears before further flight. (b) Within 50 hours' time in service after the effective date of this AD, modify the landing gear in accordancewith Part II of Aero Commander Service Bulletin No. 83 dated September 13, 1963, or FAA approved equivalent. Stamp the letter "A" after the design number on each landing gear data plate after the modification is made. This directive effective February 20, 1964.
63-27-03: 63-27-03 PIPER: Amdt. 661 Part 507 Federal Register December 24, 1963. Applies to All Models PA-24 and PA-24-250 Aircraft, Which Have 25 Ampere Circuit Breakers in the Landing Gear Retraction Motor Circuit. Compliance required within the next 100 hours' time in service after the effective date of this AD. Inadvertent tripping of the 25 ampere landing gear retraction circuit breaker has resulted in stoppage of the landing gear retraction mechanism in other than the fully extended position. Therefore, in order to eliminate this condition, with its associated hazard of partial-gear-down landing accidents, the 25 ampere circuit breaker in the landing gear retraction motor circuit must be replaced with a 30 ampere circuit breaker, Piper P/N 454661, or FAA approved equivalent. (Piper Service Letter No. 356, dated March 31, 1961, pertains to this same subject.) This directive effective January 23, 1964.
2001-15-04: This amendment supersedes an existing airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that currently requires repetitive inspections of the left and right roll spoiler actuators to check for signs of leakage and deformation of the housing, repetitive inspections of the gap between the left roll spoiler actuator housing cap and the actuator housing, repetitive torque checks of the left roll spoiler actuator housing cap attachment screws, and corrective action, if necessary. This amendment requires replacement of the double shuttle valves in the roll spoiler actuators with new improved valves, which constitutes terminating action for the requirements of this AD. 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 oil leakage from the roll spoiler actuators, which could result in incorrect roll spoiler operation and reduced controllability of the airplane.
2015-11-09: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (type certificate previously held by Schweizer Aircraft Corporation) (Sikorsky) Model 269D and Model 269D Configuration A helicopters. This AD requires reducing the life limit of the ring gear carrier assembly. This AD was prompted by cracks in the ring gear carrier assembly. The actions are intended to reduce the life of the ring gear carrier assembly to prevent failure of the main rotor transmission, loss of engine power to the main rotor, and subsequent loss of control of the helicopter.
63-24-03: 63-24-03 PIPER: Amdt. 649 Part 507 Federal Register November 27, 1963. Applies to All Models PA-23 and PA-23-160 Aircraft. Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the past 50 hours' time in service. Every 100 hours' time in service thereafter comply with paragraphs (b), (c), and (d). Several failures of the rudder trim tab actuating rod, Piper P/N 17271-00, through the bend radius of the forward hooked end and a disconnection due to a lost cotter pin have resulted in free trim tabs oscillating the rudder. Therefore, the following must be accomplished: (a) Remove the rudder trim tab control rod assembly from the aircraft. (b) Visually inspect for cracks in the area of the hooked end using a magnifying lens of at least 10-power. (c) Check the hooked end for wear in excess of 0.040 inch in the area of contact with the jackscrew. (d) Rudder trim tab control rods with cracks, or wear in excess of 0.040 inch shall be replaced before further flight. (e) Redrill the cotter pin hole in the hooked end to 0.081 inch-diameter and reinstall the rudder trim tab control rod assembly using a roll pin, Piper P/N 480728, and 0.032 inch- diameter steel safety wire, in lieu of the cotter pin. (Piper Service Letter No. 407, dated October 4, 1963, which pertains to this same subject, outlines and illustrates inspection and installation methods.) This directive effective November 27, 1963.
96-09-26: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, and Model F27 Mark 050 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.
2005-07-05: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-45A, CF6-50A, CF6-50C, and CF6-50E series turbofan engines that have not incorporated GE Service Bulletin (SB) No. CF6-50 S/B 72-1239, Revision 1, dated September 24, 2003, or that have not incorporated paragraph 3.B. of GE SB No. CF6-50 S/B 72- 1239, original issue, dated May 29, 2003. This AD requires inspecting the stage 1 low pressure turbine (LPT) blades for damage and replacement of the LPT module if necessary. This AD results from a report of a stud that separated from a turbine mid frame (TMF) strut and from an updated analysis of strut stud failures. We are issuing this AD to prevent uncontained failure of the engine and possible damage to the airplane caused by failure of TMF strut studs.
2016-04-09: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 900EX and FALCON 2000EX airplanes. This AD was prompted by a report of significant fuel leakage at the middle position of the left outboard slat. This AD would require modifying the assembly of the slat extension mechanical stop. We are issuing this AD to prevent failure of the assembly of the slat extension mechanical stop, which if not corrected, could lead to a significant fuel leak and result in an uncontained fire.
2005-11-07: The FAA adopts a new airworthiness directive (AD) for certain Extra Flugzeugproduktions-und Vertriebs-GmbH (EXTRA) Models EA-300, EA- 300S, EA-300L, and EA-300/200 airplanes. This AD requires you to seal with firewall sealant the gaps between the bottom fuselage cover (belly fairing) and the firewall and repeat the sealing procedure whenever you install the bottom fuselage cover (belly fairing). This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent fuel from flowing behind the firewall in the case of a fuel leak. This could result in an in-flight fire, which could cause loss of the airplane and crew.
2005-11-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 727-200 series airplanes equipped with a No. 3 cargo door. This AD requires repetitive detailed and high frequency eddy current inspections for cracking of the forward, lower corner frame and forward end of the lower beam of the No. 3 cargo door, and corrective actions if necessary. The AD provides an optional terminating action for the repetitive inspections. This AD is prompted by reports of cracking at the forward, lower corner frame and lower beam of the No. 3 cargo door. We are issuing this AD to detect and correct cracking of the forward, lower corner frame and forward end of the lower beam of the No. 3 cargo door, which could result in failure of the affected door stops, loss of the cargo door, and consequent rapid decompression of the airplane.
97-13-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 340B and Model SAAB 2000 series airplanes, that requires a one-time inspection to determine if certain switches are installed on the fire handle of the fire handle assembly; and replacement of the fire handle panel with a new fire handle panel, if necessary. This amendment is prompted by a report indicating that, during manufacture, a batch of defective switches were installed on certain fire handle panels on these airplanes. The actions specified by this AD are intended to ensure the proper switches are installed in the fire handle assembly. A defective switch in the fire handle assembly could prematurely fail and, consequently, prevent the proper operation of the engine fire protection system in the event of a fire.
67-02-01: 67-02-01 BOEING: Amdt. 39-335 Part 39 Federal Register January 4, 1967. Applies to Model 727 Series Airplanes Listed in Boeing Service Bulletin No. 55-15. \n\n\tCompliance required as indicated. \n\n\tCracks have occurred on flanges of the trailing edge hinge fittings of the stabilizer ribs at specific stations and on the stabilizer trailing edge beam. These failures have been attributed to high frequency oscillation of the closing panels and the trailing edge beam. In order to correct this problem, accomplish the following or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region: \n\n\t(a)\tWithin 200 hours' time in service after the effective date of this AD, unless already modified in accordance with (c), and at intervals not to exceed 200 hours' time in service thereafter, comply with either (1) or (2). \n\n\t\t(1)\tUsing eddy current methods inspect for cracks in the stabilizer trailing edge lower beam at Elevator Stations 173.21 and 209.96, in the lower flange of the hinge fitting at Elevator Stations 50.50, 99.79, 136.50, and 173.21 and in the upper flange of the hinge fitting at Elevator Station 50.50 at the fastener locations. \n\n\t\t(2)\tVisually inspect for cracks in the stabilizer trailing edge lower beam at Elevator Stations 173.21 and 209.96, in the lower flange of the hinge fitting at Elevator Stations 50.50, 99.79, 136.50, and 173.21 and in the upper flange of the hinge fitting at Elevator Station 50.50 at the fastener locations. Indication of a crack may be confirmed by a dye penetrant inspection. \n\n\t(b)\tRepair cracked parts before further flight in accordance with a repair approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(c)\tWhen an airplane has been modified in accordance with Paragraph II of Service Bulletin 55-7 and Paragraph II of Service Bulletin 55-15, or FAA-approved revisions to these Service Bulletins, the repetitive inspections specified herein may be discontinued. When an airplane has been modified in accordance with Paragraph II of Service Bulletin 55-7 only, or FAA-approved revision to this Service Bulletin, the repetitive inspections specified herein for Elevator Stations 50.50, 99.79, and 136.50 may be discontinued. Immediately prior to accomplishing any modification, inspect in accordance with either (a)(1) or (a)(2) and if cracks are found, repair in accordance with (b). \n\n\tThis supersedes AD 64-17-02. \n\n\tThis directive effective February 3, 1967.
71-08-02: 71-08-02 MCDONNELL DOUGLAS: Amend 39-1189 as amended by amendment 39-1346. Applies to DC-9 airplanes certificated in all categories. \n\n\tCompliance required within the next 50 hours' time in service after effective date of this AD, unless already accomplished. \n\n\tTo ensure pilot control of speed brake retraction and to prevent inflight deployment of ground spoilers, accomplish one of the following: \n\n\t1.\tAffix a placard(s) in the cockpit in plain view of both crew members stating: \n\n\t\tDO NOT EXTEND GEAR WITH SPEED BRAKES DEPLOYED \n\n\t\tDO NOT ARM GROUND SPOILERS PRIOR TO GEAR EXTENSION \n\n\t2.\ta. Install the interlock switch per McDonnell Douglas DC-9 Service Bulletin No. 32-128, dated November 17, 1971, or later FAA approved revisions, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region and \n\n\t\tb.\tAmend the Limitations Section, FAA Approved Airplane Flight Manual, to include the statements: \n\n\t\t\tDo not extend gear withspeed brakes deployed. \n\n\t\t\tDo not arm ground spoilers prior to gear extension. \n\n\tNOTE: Placards previously installed per Step 1. may be removed if step 2 is accomplished. \n\n\tAmendment 39-1189 became effective April 13, 1971. \n\n\tThis amendment 39-1346 becomes effective November 30, 1971.
63-07-03: 63-07-03 PIPER: Amdt. 551 Part 507 Federal Register April 4, 1963. Applies to All Models PA-23 and PA-23-160 Aircraft. Compliance required as indicated. Cracks and loose or working rivets have been found in the attachment area of the rudder trim tab horn, P/N 17059-00, to the rudder trim tab skin, P/N 17068-27. Cracked rudder trim tab ribs P/N 17068-17 also have been found. To preclude the separation of the trim tab horn from the trim tab, accomplish the following: (a) On aircraft having 690 or more hours time in service on the effective date of this AD, within the next 10 hours' time in service unless already accomplished within the last 90 hours' time in service and within each 100 hours' time in service thereafter from the last inspection, accomplish the inspection specified in (c). (b) On aircraft having less than 690 hours' time in service on the effective date of this AD, accomplish the inspection specified in (c) between 600 and 700 hours' time in service and within each 100 hours' time in service thereafter from the last inspection. (c) Visually inspect with at least a 10-power magnifying glass the rudder trim tab horn attach rivets for looseness or evidence of rivet working and the adjacent tab skin for cracks. (d) If skin cracks, loose or working rivets are found, visually inspect the rudder trim tab support rib, P/N 17068-17 for cracks. (e) If any of the defects mentioned herein are found, repair in accordance with Civil Air Regulations Part 18 or replace the affected part, or parts, with an airworthy assembly prior to further flight. (Piper's Periodic Inspection Report pertains to this same subject.) This directive effective April 15, 1963.
2005-11-05: The FAA adopts a new airworthiness directive (AD) for all airplanes equipped with Precise Flight, Inc. (Precise Flight) Models SVS I and SVS IA standby vacuum systems (SVS) installed under certain supplemental type certificates or through field approval. This AD requires you to replace the airplane flight manual supplement (AFMS) in the airplane flight manual with the appropriate revision and install placards as defined in the AFMS, upgrade the Model SVS I or SVS IA SVS to the Model VI SVS, and add the instructions for continued airworthiness (ICA) to the maintenance schedule for the aircraft. This AD results from several reports of failed shuttle control valves of the standby vacuum system (SVS) and one report of an airplane crash with a fatality in which improper use of the SVS was a factor. We are issuing this AD to correct problems with the SVS before failure or malfunction during instrument flight rules (IFR) flight that can lead to pilot disorientation and loss of control of the aircraft.
2005-11-11: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400, -401, and -402 series airplanes. This AD requires repetitive inspections to detect discrepancies of the attachment fittings of the outboard flap front spar at flap track Number 4 and Number 5 locations, and corrective actions if necessary. This AD also requires eventual replacement of the attachment fittings as terminating action for the repetitive inspections. This AD is prompted by the discovery of several airplanes that have loose flap front spar attachment fittings at flap track Number 4 and Number 5 locations. We are issuing this AD to prevent the attachment fittings from becoming detached, and consequent loss of control of the airplane.
71-17-08: 71-17-08 CESSNA: Amdt. 39-1273. Applies to Model 337 Airplanes. Compliance. To minimize the possible adverse affects of undetected rear engine stoppage during take-off, within the next 10 hours' time in service after the effective date of this AD, the following modifications must be accomplished and the following operational procedures will be applicable: A) Readjust the rear engine idle RPM from 575-625 to 625-675 and readjust idle mixture accordingly. B) Taxi primarily by use of the rear engine. C) Initiate all take-offs by advancing the throttle on the rear engine to a point where the normal functioning of the rear engine has been established before advancing the throttle of the front engine. D) Install a permanent placard to the right of the tachometer instrument to read as follows: TAXI AND TAKE-OFF LEAD WITH REAR ENGINE POWER CHECK RPM AND FUEL FLOW NOTE: The operator may make and install a temporary placard using minimum 1/8 inch highletters until the permanent placard is obtained from the manufacturer and properly installed. Cessna Service Letter ME 71-21 refers to the subject matter of this AD. This amendment becomes effective August 24, 1971.