Results
99-02-09: This amendment adopts a new airworthiness directive (AD), applicable to Agusta S.p.A. Model A109C and A109K2 helicopters. This amendment requires removing the main rotor pitch link assemblies, measuring the radial play of the upper and lower spherical bearings (bearings), and replacing any unairworthy bearings. This amendment is prompted by four reports of increased vibration of the helicopters caused by wear in the bearings of the main rotor pitch change link assembly. The actions specified by this AD are intended to detect unairworthy bearings on the pitch change link assembly and to prevent increased vibration and subsequent reduced controllability of the helicopter.
2007-08-03: The FAA is adopting a new airworthiness directive (AD) to supersede AD 2006-17-04, which applies to certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, T182T, 206H, and T206H airplanes. AD 2006-17-04 currently requires you to inspect the two end fittings on each of the flexible fuel hoses located in the engine compartment for the correct torque values, and, if any incorrect torque values are found during the inspection, tighten the hose end fittings to the correct torque values. This AD results from four reports of loose fuel lines connected to the fuel servo or fuel flow transducer. Two reports were of in-flight engine failure on a Model T182T airplane. A third report was of in-flight engine failure on a Model 206H airplane. A fourth report was of a Model 172S airplane losing engine power on final approach. Consequently, this AD would require you to establish the correct torque values of the end fittings on fuel hoses for certain Cessna Models 172R, 172S, 182T,T182T, 206H, and T206H airplanes. This AD clarifies that the torque values need to be physically established and visual inspection only is not sufficient. We are issuing this AD to detect and correct potential loss of fuel flow, which may result in partial or complete loss of engine power and/or uncontrolled engine compartment fire due to fuel leakage forward of the firewall.
2000-25-01: This amendment supersedes Airworthiness Directive (AD) 80-26-05, which currently requires you to repetitively inspect the main landing gear (MLG) inboard door hinges and attachment angles for cracks on certain The New Piper Aircraft, Inc. (Piper) PA-31 series airplanes. AD 80-26-05 also requires you to replace any cracked MLG inboard door hinge or attachment angle with parts of improved design. This AD results from the Federal Aviation Administration's policy on aging commuter-class aircraft and the determination that an improved design MLG inboard door hinge and attachment assembly, when incorporated, will eliminate the need for the currently required repetitive short-interval inspections; however, we have received reports of cracks in the improved design MLG inboard door hinge assemblies on the affected airplanes. This AD retains the current repetitive inspections contained in AD 80-26-05, and requires inspections on the improved design parts. The actions specified by this AD are intended to detect and correct cracked MLG inboard door hinge assemblies. These cracked door hinge assemblies could result in the MLG becoming jammed, with consequent loss of control of the airplane during landing operations.
2018-01-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes); and Airbus Model A310 series airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by reports of the portable oxygen cylinder assembly (POCA) slipping from its bracket inside a one- frame overhead stowage compartment. We are issuing this AD to address the unsafe condition on these products.
97-14-11: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 97-14-11 that was sent previously to all known U.S. owners and operators of certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) series airplanes by individual notices. This AD requires repetitive inspections to detect cracks of a certain bulkhead web of the fuselage at certain locations, and repair, if necessary. This action is prompted by a report of a pressurization problem during flight, which was caused by fatigue cracking in the underfloor pressure bulkhead of the fuselage. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in uncontrolled depressurization of the airplane and/or reduced structural integrity of the fuselage.
2007-08-02: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. model HC-E4A-3( )/E10950( ) propellers. This AD requires initial and repetitive inspections and rework of the propeller blade retention radius, and replacement of the propeller blade thrust bearing, for each blade. This AD results from reports of excessive propeller vibration and of damaged or broken propeller blade thrust bearings found during routine and investigative propeller disassembly. We are issuing this AD to prevent propeller blade separation, damage to the airplane, and possible loss of airplane control.
95-10-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A300, A300-600, and A310 series airplanes, that requires inspections to detect cracks in the lower spar axis of the pylon between ribs 9 and 10, and repair, if necessary. This amendment is prompted by a report indicating that fatigue cracks have been found on the lower spar of the pylon. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the lower spar of the pylon.
2000-25-03: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Inc. (BHTI) Model 205A-1, 205B, 212, 412, and 412CF helicopters. This action requires inspecting the locking washer on each main rotor actuator (actuator) for twisting or damage to the tab and replacing any locking washer that has a twisted or damaged tab. Replacing certain locking washers, regardless of condition, is also required within a specified time period. Installing a certain airworthy locking device on each actuator constitutes terminating action for the requirements of this AD. This amendment is prompted by an incident in which a damaged locking washer allowed the rod end to detach from the collective actuator, causing loss of collective control of the main rotor. The current locking washer is subject to mechanical damage and failure, which allows the actuator piston to unthread itself from its rod end. This condition, if not corrected, could cause loss of control of the main rotor and subsequent loss of control of the helicopter.
2004-13-08: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 series airplanes. This AD requires inspection of the welded joints of the balance weight brackets for the left and right elevator trim tabs for cracking; repetitive inspections, as applicable; and corrective actions including the eventual replacement of all brackets, which constitutes terminating action for the repetitive inspections. This action is necessary to prevent the loss of the balance weight for the elevator trim tab, which could result in incorrect trim during takeoff and landing, and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2017-24-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracking in the upper aft skin at the rear spar of the wings. This AD requires repetitive inspections for cracking of the upper aft skin of the wings, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2000-25-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes, that currently requires a one-time inspection of the coupling hinge and locking fastener of the Gamah couplings of the fuel system tubing located in the wing dry bay to detect discrepancies, and follow-on corrective actions. This amendment retains those requirements and adds a requirement to revise the applicability of the existing AD to add certain airplanes. The actions specified in this AD are intended to prevent failure of the rivets of the Gamah couplings and consequent separation of a Gamah coupling, which could result in fuel leakage and consequent fire in or around the wing. This action is intended to address the unsafe condition.
2017-26-05: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Models G-1159A (GIII), G-IV, and GIV-X airplanes. This AD was prompted by a report that certain flap tracks were manufactured with the upper flange thickness less than design minimum. This AD requires replacing any defective flap track. We are issuing this AD to address the unsafe condition on these products.
2000-24-03: This amendment supersedes an existing airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with additional information regarding procedures to ensure complete pressurization of the hydraulic lines for the flaps. This amendment requires revising the existing AFM revision to include a flap system test to be performed prior to the first flight of the day. This amendment also requires, for certain airplanes, modification of the flap actuators of the flight controls. The actions specified by this AD are intended to prevent an uncommanded retraction of the flaps during takeoff, which could result in an aborted takeoff and consequent potential for runway overrun.
86-25-07: 86-25-07 ROLLADEN-SCHNEIDER FLUGZEUGBAU GmbH: Amendment 39-5487. Applies to Model LS-6, all serial numbers. Compliance is required prior to further flight, after the effective date of this AD, unless already accomplished. To prevent possible damage of the control stick, accomplish the following: a) Remove Bezel from airspeed indicator and mask out the red arc with tape that would not interfere with airspeed indictor needle and readability of the instrument. b) Replace Bezel to airspeed indicator and mark a red radial line on the face of the Bezel 0.05" wide, 0.30" long at 200 km/h (108 kts) establishing a new maximum airspeed limit. c) Install a placard on the instrument panel in clear view of the pilot which states: "Maximum Airspeed (IAS): 200 km/h (108 kts)." d) On existing placard mask out with tape the yellow arc limitations 108 - 146 kts, and the following red arc airspeed indicator markings: Vne 6500 Ft 146 kts Vne 6501-9800 Ft 139kts Vne 9801-19700 Ft 118 kts e) Flight manual pages 2.2, Limitations; page 2.3, Airspeed Indicator Markings; page 2.7, Placards, are obsolete. f) Attach a copy of this Airworthiness Directive to the Flight Manual. NOTE: Rolladen-Schneider Technical Bulletin No. 6009 dated July 7, 1986, applies to this AD. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium 09667-1011; telephone 513.38.30 Ext 2710, or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, telephone (516) 791-6220. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations 21.197 and 21.199 to a base where the AD can be accomplished. This amendmentbecomes effective December 30, 1986.
2000-24-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time detailed visual inspection to detect discrepancies of all electrical wiring installations in various areas of the airplane; and corrective actions, if necessary. This amendment is necessary to prevent electrical arcing and/or heat damaged wires due to improper wire installations during manufacture and/or maintenance of the airplane, and consequent fire and smoke in various areas of the airplane. This amendment is intended to address the identified unsafe condition.
98-14-08: 98-14-08 ROBINSON HELICOPTER COMPANY: Docket No. 98-SW-30-AD. Applicability: Model R22 helicopters, with forward flexplate, part number (P/N) A947-1 A through D, or P/N A193-1, installed, certificated in any category. NOTE 1: This AD applies to each helicopter 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 helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by thisAD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. Compliance: Required within 25 hours time-in-service (TIS) or 15 calendar days, whichever occurs first, unless accomplished previously. To prevent failure of the flexplate, which could result in failure of the main rotor drive system and subsequent loss of control of the helicopter, accomplish the following: (a) Remove the flexplate and replace it with an airworthy flexplate, P/N A947-1 E or F, in accordance with the following: (1) With the clutch disengaged, support the forward end of the clutch shaft, P/N A166-1, and remove the forward flexplate, P/N A947-1 or A193-1, and the intermediate flexplate, P/N A947-2 or P/N A193-2. Record any shim locations for reinstallation. (2) Install a zero TIS forward flexplate, P/N A947-1 E or F, and any shims that were noted. Use washers, P/N AN960-516 or AN960-516L, under the nut so that 2-4threads are exposed. Torque the fasteners. (3) Inspect the sheave alignment. (4) Inspect the clutch shaft, P/N A166-1, angle. (5) Reinstall the intermediate flexplate and shim. NOTE 2: Robinson R22 Maintenance Manual, Sections 1.320, 7.230, 7.240, and 7.330 pertain to paragraphs (a)(2), (a)(3), (a)(4), and (a)(5) of this AD, respectively. NOTE 3: Robinson Helicopter Company R22 Service Bulletin SB-75, dated November 22, 1994, pertains to the subject of this AD. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. NOTE 4: Information concerning the existence of approved alternative methods of compliance with thisAD, if any, may be obtained from the Los Angeles Aircraft Certification Office. (c) 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 helicopter to a location where the requirements of this AD can be accomplished. (d) Priority Letter AD 98-14-08, issued June 25, 1998, becomes effective upon receipt.
97-13-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires loosening certain nuts on the horizontal stabilizer control unit (HSCU) to reduce stress on bolts; a one-time inspection of certain bolts on the HSCU to detect cracking, and replacement, if necessary; application of corrosion protection to these bolts; and reassembly and reidentification of the modified HSCU. This amendment is prompted by reports indicating that stress corrosion, resulting from overtightening of nuts on these bolts, has caused some of these bolts to crack and fail. The actions specified by this AD are intended to prevent failure of these bolts because of stress corrosion cracking which, if not corrected, could lead to loss of control of the horizontal stabilizer and reduced controllability of the airplane.
2007-07-13: 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: Avionics and electrical wire harnesses are routed behind the Primary Flight Displays (PFD) tray at the rear of the instrument panel. In some cases, the wire harness has been found to be chafing on the PFD tray. That could result in electrical arcing and shorting and subsequent loss of systems essential for safe flight. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2000-24-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracking of the frame web, doubler, and inner chord of the forward edge frame of main entry door number 1, and various follow-on actions. This amendment is prompted by reports of cracking in the frame web, doubler, inner chord, and strap of the forward edge frame of main entry door number 1. The actions specified by this AD are intended to prevent cracks in the frame web and doubler of the forward edge frame of main entry door number 1, which could result in inability of the edge frame to react door stop loads, and consequent rapid depressurization of the airplane.
2017-26-04: We are superseding Airworthiness Directive (AD) 2009-25-07 for Airbus Helicopters Model EC120B helicopters. AD 2009-25-07 required amending the rotorcraft flight manual supplement (RFMS) and pre-flight checking the emergency flotation gear before each flight over water. Since we issued AD 2009-25-07, Airbus Helicopters developed a terminating action and identified an additional part- [[Page 60293]] numbered emergency floatation gear part with the unsafe condition. This new AD retains the requirements of AD 2009-25-07, expands the applicability, and adds a terminating action for the repetitive inspections. The actions of this AD are intended to correct an unsafe condition on these helicopters.
87-02-04: 87-02-04 BRITISH AEROSPACE: Amendment 39-5497. Applies to Models HP 137 Mk.1 (all serial numbers), Jetstream Series 200 (all serial numbers), and Jetstream Model 3101 airplanes (serial numbers 601 to 606) equipped with Main Landing Gear Type Numbers 1863 and 1864 (all suffixes), certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent the development of hazardous cracks in the main landing gear pintle housing, accomplish the following: (a) Within 300 landings and every 1200 landings thereafter: Conduct an eddy current inspection in accordance with Section 2 "Accomplishment Instructions", Part A "Non- destructive Testing" of British Aerospace (BAe) Mandatory Service Bulletin (MSB) No. 32-A- JA851226 dated December 19, 1985, Section 2 "Accomplishment Instructions" of BAe Air Weapons Division (AWD) Service Bulletin (S/B) No. 32-19 dated December 19, 1985. If cracks are found, before further flight, carry out repairs in accordance with AWD S/B No. 32-19. (b) At intervals of 300 landings after the initial inspection, required by paragraph (a) of this AD, conduct a visual inspection in accordance with Section 2 "Accomplishment Instructions," Part B, "Visual Inspections" of AWD S/B No. 32-19. If indications of cracks are discovered, conduct an eddy current inspection in accordance with paragraph (a) of this AD. If cracks are found, before further flight, carry out repairs in accordance with AWD S/B No. 32-19. (c) Within 300 landings after a heavy or abnormal landing, conduct an eddy current inspection in accordance with paragraph (a) of this AD. (d) If the actual number of landings is unknown for the purpose of complying with this AD, one landing may be substituted for each one-half hour of flight unless the operator substantiates a different flight hours to landings ratio. This substantiation must be submitted to, and approved by, the Manager, Aircraft Certification Staff, address below. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishment of these inspections concurrent with other scheduled maintenance on the airplane. (g) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the documents referred to herein upon request to British Aerospace, Engineering Department, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041; Telephone (703) 435-9100; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 30, 1987.
2007-07-14: The FAA is adopting a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ airplanes. This AD requires modifying the forward and aft auxiliary fuel tanks. This AD results from a fuel system reassessment according to SFAR 88 criteria, which revealed the possibility of sparks due to chafing between the harnesses of the forward and aft auxiliary fuel tanks, between certain harnesses attached to the aircraft structure, or between certain harnesses attached to certain mechanical components. We are issuing this AD to prevent a potential ignition source inside a fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion.
2000-24-20: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 707 and 720 series airplanes, that requires repetitive inspections of certain stringers and around certain fastener holes of the lower skin of the wings to detect fatigue cracking, and repair, if necessary. This action is necessary to detect and correct such cracking and consequent damage to adjacent structure, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2000-24-17: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires deactivation of the forward and center cargo control units (CCU). This amendment requires, among other actions, a general visual inspection to verify that all six external connectors of suspect CCU's have a certain part number stamped on the connector bodies on all CCU assemblies, and follow-on actions, which would constitute terminating action for the deactivation requirements. The actions specified by this amendment are intended to prevent overheating of the electrical pins inside the CCU's and subsequent release of hot gases and flames, which could result in smoke and fire in the cargo compartment.
2011-08-08: 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: It has been found occurrence of screw units manufactured with metallographic non-conformity that may increase their susceptibility to brittle fracture. The screw failure may result in loss of the related balance washer causing a possible ram air turbine (RAT) imbalance event, which may result in RAT structural failure, which associated with an electrical emergency situation, could result in loss of power to airplane flight controls hydraulic back-up system. * * * * * Loss of power to the hydraulic back-up system for airplane flight controls could reduce the ability of the flightcrew to maintain the safe flight and landing of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. [[Page 20504]]