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90-07-08 R1: 90-07-08 R1 S.E.L.A. LABORATOIRE ABADIE (SELA): Amendment 39-6546 as revised by Amendment 39-6627. Applicability: Fluorescent lighting lamp connectors, Part Number (P/N) 3185-1A, and Remote Power Units (RPU), P/Ns TR 992, TR 992A, TR 992-1, TR 992-3, TR 992-4, and TR 992-5, manufactured by SELA, and installed in, but not limited to AMD-BA Falcon Models 10, 20, 50, 900, BAe Jetstream Models 3101 and 3201, CASA Model 235, Embraer Model EMB-120, and SAAB-Scania Model SF 340A airplanes certificated in any category. NOTE 1: SELA and Aerospace Lighting Corporation (ALC) components are similar in size, shape and color and have similar part numbers. They may be identified by trademark. The SELA RPU can be identified by a starburst pattern incorporating the text "laboratoire, abadie, France." The ALC RPU can be identified by a stylized ALC logo with "Aerospace Lighting Corp" in smaller print beneath the logo. The ALC lamp connector has "ALC" molded into the gray body of theconical piece of the connector body with a black lock ring. The SELA lamp connector is stamped in yellow ink on a black connector body with a gray lock ring. The ALC lamp can be positively identified by the presence of a small hole in the locking channel of each blue plastic end piece. Compliance: Required as indicated in the body of the AD, unless already accomplished per AD 90-07-08. To prevent smoke, fire, and possible electrical shock, or electromagnetic interference to flight critical or essential systems, accomplish the following: (a) If the cabin fluorescent lighting system is not deactivated, within the next 30 days after the effective date of this AD, and thereafter until the actions described in paragraph (b) of this AD are accomplished, insert a copy of this AD into the limitations section of the airplane flight manual, and prior to each takeoff where cabin fluorescent lights are used: Visually check the cabin fluorescent lighting, and remedy as follows:(1) Replace all failed lamps prior to further flight. (2) Replace all failing lamps which have noticeably less illumination (darker) than adjacent lamps within the next 10 hours time-in-service after the lamp condition is found. (b) If the cabin fluorescent lighting system is not deactivated, within the next 120 days after the effective date of this AD, visually inspect all cabin fluorescent lighting system components, and prior to further flight remedy all defects found following the instructions in this AD. If the cabin fluorescent lighting system is deactivated as described in paragraph (c) of this AD, the inspection described in this paragraph is not required until the fluorescent lighting system is reactivated. NOTE 2: The aircraft manufacturer's maintenance manual, the installer's maintenance manual, other service information, SELA Technical Data Sheet (TDS) REF 90/11980, dated February 9, 1990, or Bigorre Aerospace Corporation (BAC) "How To" Number 1Manual, dated May 10, 1989, contains information which supplements the instructions described in this AD. This information is important to proper maintenance and replacement of defective components. (1) Insure that the aircraft manufacturer's instructions regarding electrical safety precautions are followed. NOTE 3: Hazardous voltages may exist in the fluorescent lighting system. (2) Visually inspect all installed SELA RPUs (P/Ns) TR992, TR 992A, TR 992-1, TR 992-3, TR 992-4, and TR 992-5 wiring harnesses: (i) If charred, burned, or peeling insulation on wires is found, replace the RPU assembly as a unit. No repairs of the high voltage wires may be made except for the installation of the lamp connector. (ii) Remove and discard any foil insulation installed around the RPU. (iii) Remove all tywraps where wires may be bundled together and inspect the wire insulation for crimps, kinks, or abrasion. Replace the RPU if the insulation is damaged. Donot fold the wire harness against itself. (iv) Insure that the wire insulation is protected from abrasion against the aircraft structure by use of grommets, standoffs, or similar items. (v) Measure the length of the output wires from the RPU termination to the lamp connectors. Insure that each high voltage wire does not exceed 78 inches (2M) in length. If the wire exceeds 78 inches, cut the lamp connector end of the wire and install a new fitting (P/N 3185-5) by stripping between 0.12 inch (3mm), and 0.20 inch (5mm) of the insulation from the end of the wire and crimping the fitting onto the wire with Deutsch crimping pliers P/N 15500 and SELA positioner P/N 3185-8 in place of Deutsch positioner 20 MS (red), or Burndy M10S-1 crimping tool with S-6A die, or SELA/BAC approved equivalent. Do not solder the wire into the fitting. (3) Each lamp shall be installed only into 2 connectors made by the same manufacturer as the lamp. (4) Visually inspect all lamp connector assemblies and for each such assembly: (i) Replace all burned, melted, cracked, or incorrectly installed lamp connectors, (SELA TDS REF 90/11980 dated February 9, 1990, provides installation criteria). (ii) Insure that the lamp connector spring (P/N 3185-22), is free to move within the connector, is unbroken and undamaged, and the wire does not bind within the connector. After the lamp connector is correctly installed on the lamp, the spring will not move freely. (iii) Insure that the contact fitting (P/N 3185-5) is properly crimped and is not soldered onto the wire. (iv) Insure that the contact fitting is installed flush over the end of the lamp contact with no gap between the fitting and the mating end of the lamp. (v) Insure that the lamp connector body (P/N 3185-7) is installed first over the lamp until it "clicks" into position. There should be no more than a 0.04 inch (1mm) gap between the connector body and the lamp end. Slide thelocking sleeve (P/N 3185-15) over the connector body. Do not slide the locking sleeve onto the connector before installation on the lamp. (vi) Insure that there are no bare wires or stray wire strands at the end of the connector after assembly. NOTE 4: High voltage potentials may exist between adjacent output wires and hasten the formation of arcing damage. (5) Insert the lamp into no more than 2 clips insuring a snug fit. Insure that lamp clips are properly secured to the airplane structure. Reposition any lamps that contact this structure. (c) The cabin fluorescent lighting system may be deactivated in accordance with the following instructions: (1) If the deactivation is accomplished by tripping a circuit breaker (CB), then the CB must be tywrapped in the tripped position, or a collar installed which prevents resetting of the CB. NOTE 5: Some airplane installations may power this system through more than one switch or circuit. In those cases,the fluorescent lighting system power lead must be removed, capped, and stowed so that no combination of switch selections will power the cabin fluorescent lights. (2) A placard is placed in proximity to the cabin fluorescent lighting system control stating that the system is deactivated. (3) That prior to each boarding of passengers at night or during reduced light conditions, the flight crew must ensure that one passenger reading light per row and all vestibule lights are illuminated. (4) That prior to deplaning passengers at night or during reduced light conditions, the flight crew: (a) Request that all passengers turn on the reading light above their seat, and (b) Ensure that the vestibule lighting is illuminated. (5) All other cabin lights are required to be operable. (d) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) The visual check, only, required by paragraph (a) of this AD, may be accomplished by a certificated flightcrew member. NOTE 6: When the checks required by paragraph (a) of this AD are accomplished by a flightcrew member pursuant to the restrictions specified in paragraph (e) of this AD, maintenance records must be maintained as required by FAR 91.173, 121.380, or 135.439 as applicable and a maintenance record is not required unless a defect is found. (f) An alternate method of compliance or adjustment of the compliance times which provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. NOTE 7: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. All persons affected by this directive may obtain copies of the documents referred to herein upon request to S.E.L.A. Laboratoire Abadie, BP No. 1 65500, Vic En Bigorre, France; Telephone (33) 62.96.71.56; Facsimile (33) 62.96.23.09, or Bigorre Aerospace Corporation (BAC), Suite 1107, 6543-46th Street North, Pinellas Park, Florida 34665; Telephone (813) 525-8115; Facsimile (813) 522-5820; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment revises AD 90-07-08, Amendment 39-6546. This amendment (39-6627, AD 90-07-08 R1) becomes effective on July 2, 1990.
98-18-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that requires modification of the wiring of the strake ice protection system (SIPS). This amendment is prompted by a report of a fire in the electrical and electronic compartment of a Model MD-90-30 series airplane. The actions specified by this AD are intended to prevent an electrical short circuit of the wiring of the SIPS, which could result in a fire in the electrical and electronic compartment of the airplane.
2018-04-03: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. This AD was prompted by a report that a jammed control cable prevented the full extension of the nose landing gear (LG). This AD requires a general visual inspection of the LG handle teleflex cable conduit connector for the presence of a grease nipple, a maintenance records check of affected airplanes, a detailed inspection for [[Page 7969]] corrosion and damage of the LG handle teleflex cable, and corrective actions if necessary. This AD also requires revising the maintenance or inspection program, as applicable. We are issuing this AD to address the unsafe condition on these products.
2003-08-05: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires inspecting the ASU No. 2 printed circuit board (PCB) to determine if the resistor R8 is installed, and if it is not installed, replacing the PCB with an airworthy PCB with that resistor installed. This amendment is prompted by the discovery of a PCB without a critical resistor that polarizes the voltage regulator that regulates electrical power to a critical warning light, a critical caution light, and the main rotor revolutions per minute (RPM) signal to the vehicle engine management display (VEMD). The actions specified by this AD are intended to prevent the malfunction of the two critical lights and the rotor RPM signal to the VEMD, failure of these components to timely alert the pilot to the associated malfunctions, further helicopter damage because of these malfunctions, and subsequent loss of control of the helicopter.
96-14-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes. This action requires modification of the radio altimeter wiring circuitry associated with the Automatic Flight Control Augmentation System (AFCAS). This amendment is prompted by a report indicating that the AFCAS does not properly monitor the radio altimeter status during automatic landing operations. The actions specified in this AD are intended to prevent erroneous indications and failure of the AFCAS to properly align, flare, and retard the airplane during automatic landing operations if a single radio altimeter were to fail.
2003-07-11: This amendment supersedes an existing airworthiness directive (AD), that is applicable to Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH) models BR700-710A1-10 turbofan engines with fan disc part numbers (P/ Ns) BRR18803, BRR19248, or BRR20791 installed, and BR700-710A2-20 turbofan engines with fan discs P/Ns BRR19248 or BRR20791 installed. That AD currently requires initial and repetitive inspections of these fan discs for cracks, and if necessary replacement with serviceable parts. This amendment requires the same inspections but with longer intervals between repetitive inspections under certain conditions, and requires removal of any dry film lubricant coating from the front face of the fan disc for visual inspections. This amendment is prompted by reevaluation by RRD of results from a fleet-wide inspection campaign, reevaluation of existing repetitive inspection interval requirements, and by a revised servicebulletin (SB) that introduces improved inspection procedures. The actions specified by this AD are intended to detect cracks in the fan disc, that could result in an uncontained engine failure and damage to the airplane.
2012-04-02: We are adopting a new airworthiness directive (AD) for all Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes; Model CL-600-2D15 (Regional Jet Series 705) airplanes; and Model CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by reports of aileron control stiffness. This AD requires revising the maintenance program to incorporate the discard task for outboard wing aileron pulleys. We are issuing this AD to prevent aileron control stiffness during flight, which could result in reduced controllability of the airplane.
98-17-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASW-19 sailplanes. This AD requires inspecting the tow release cable guide fittings for the correct mounting, and, if the fittings are mounted in the front of the bulkhead, moving the fitting to the rear of the bulkhead and adjusting the neutral travel of the cable. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent premature release of the tow cable during take-off, which could result in loss of the sailplane.
98-16-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. Model PC-7 airplanes. This AD requires replacing the seal unit on both main landing gear (MLG) legs and the nose landing gear (NLG) leg. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent MLG or NLG failure caused by deterioration of a MLG or NLG leg seal unit, which could result in damage to the airplane or airplane control problems during takeoff, landing, or taxi operations.
2012-02-17: We are adopting a new airworthiness directive (AD) for all Model 757 airplanes. This AD was prompted reports that several operators have found cracking in the front spar lower chord at the fastener locations common to the side link support fitting at wing station (WS) 292. This AD requires repetitive inspections for corrosion and cracking in this area, and corrective actions if necessary. We are issuing this AD to detect and correct such corrosion and cracking, which, if not corrected, could grow and result in structural failure of the spar.
61-22-07: 61-22-07 MOONEY: Amdt. 359 Part 507 Federal Register November 2, 1961. Applies to the M-20, M-20A, and M-20B Aircraft, Serial Numbers 1001 Through 1875. Compliance required within 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent failures of the fuel and oil pressure gage lines in the accessory compartment, the following replacement is required: Replace the copper fuel and oil pressure gage lines from the firewall to the engine pickup location with flexible hose in accordance with Mooney Service Letter 20-82A or replace with other FAA approved equivalent lines or fittings. (Mooney Service Letter 20-82A covers this same subject.) This directive effective November 2, 1961.
2003-07-14: This amendment adopts a new airworthiness directive (AD), applicable to a single McDonnell Douglas Model DC-10-30 airplane, that requires repetitive tests for electrical continuity and resistance and repetitive inspections to detect discrepancies of the fuel boost/ transfer pump connectors; and corrective actions, if necessary. This action is necessary to prevent arcing of connectors in the fuel boost/ transfer pump circuit, which could result in a fire or explosion of the fuel tank. This action is intended to address the identified unsafe condition.
80-18-08: 80-18-08 JET ELECTRONICS AND TECHNOLOGY, INC.: Amendment 39-3893. Applies to all Model PS-823( ) series Emergency Power Supplies, normally used as power supply for standby attitude indicators. Compliance is required as indicated unless already accomplished. To prevent loss of emergency electrical power and possible corrosive or thermal damage to the aircraft accomplish the following: Within the next 100 flight hours or six months time from the effective date of this AD, determine if compliance has already been accomplished by observing the modification decal on the front of the unit. If the modification number listed below has been marked off, no further action is required. JET Part No. Model Modification No. 501-1075-01 PS-823A 18 501-1075-02 PS-823B 17 501-1075-03 PS-823C 15 501-1075-04 PS-823D 14 501-1075-05 PS-823A/T 21 501-1075-06 PS-823B/T 19 501-1075-07 PS-823C/T 17 501-1075-08 PS-823D/T 16 If the applicable modificationnumber has not been marked off, install modifications in accordance with J.E.T. Service Bulletin SB501-1075-16E, dated February 28, 1979. Modifications must be made by an FAA Certified Repair Station, an FAA approve repair facility, or J.E.T. Upon submission of substantiating data, through an FAA Aviation Safety Inspector, the Chief, Engineering and Manufacturing Branch, FAA Great Lakes Region, may approved an adjustment to compliance time or an equivalent means of compliance. This amendment becomes effective August 28, 1980.
2009-11-02: The FAA is adopting a new airworthiness directive (AD) for CFM International S.A. CFM56-2, CFM56-3, CFM56-5A, CFM56-5B, CFM56-5C, and CFM56-7B series turbofan engines with certain part number (P/N) and serial number (SN) high-pressure compressor (HPC) 4-9 spools installed. This AD requires removing certain HPC 4-9 spools listed by P/N and SN in this AD. This AD results from reports of certain HPC 4-9 spools that Propulsion Technology LLC (PTLLC) improperly repaired and returned to service. We are issuing this AD to prevent cracking of the HPC 4-9 spool, which could result in possible uncontained failure of the spool and damage to the airplane.
90-15-14: 90-15-14 BOEING: Amendment 39-6665. Docket No. 89-NM-249-AD. \n\n\tApplicability: Model 737-300 and 737-400 series airplanes, equipped with Kidde engine fire and overheat detection systems, as listed in Boeing Service Bulletin 737-26-1055, Revision 1, dated September 14, 1989, certificated in any category. \n\n\tCompliance: Required within 18 months after the effective date of the AD unless previously accomplished.\n\n\tTo reduce false engine fire and overheat warnings, which could result in unnecessary engine in-flight shutdowns and airplane diversions that unduly jeopardize continued safe operation of the airplane, accomplish the following: \n\n\tA.\tModify the engine fire and overheat detection system on each engine in accordance with Boeing Service Bulletin 737-26-1055, Revision 1, dated September 14, 1989. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, SeattleAircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR Sections 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6665, AD 90-15-14) becomes effective on August 23, 1990.
74-08-09 R3: We are revising an existing airworthiness directive (AD) for transport category airplanes that have one or more lavatories equipped with paper or linen waste receptacles. That AD currently requires installation of placards prohibiting smoking in the lavatory and disposal of cigarettes in the lavatory waste receptacles; establishment of a procedure to announce to airplane occupants that smoking is prohibited in the lavatories; installation of ashtrays at certain locations; and repetitive inspections to ensure that lavatory waste receptacle doors operate correctly. This new AD extends the time an airplane may be operated with certain missing ashtrays. This AD was prompted by the determination that certain compliance times required by the existing AD could be extended and still address fires occurring in lavatories caused by, among other things, the improper disposal of smoking materials in lavatory waste receptacles. We are issuing this AD to correct this unsafe condition on these products.
98-16-20: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB 2000 series airplanes. This action requires a one-time visual inspection of the right- and left-hand propeller gearbox to ensure that the attachment nut that secures the borescope plug to the gearbox is installed; and installation of an attachment nut, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent oil leakage from the propeller gearbox, which could lead to an increase in oil temperature and result in engine shutdown.
92-09-02: 92-09-02 BOEING: Amendment 39-8227. Docket No. 91-NM-218-AD. Supersedes AD 84-03-01, Amendment 39-4803.\n\n\tApplicability: All Model 737-100 and 737-200 series airplanes, line number 001 through line number 900, certificated in any category.\n\n\tCompliance: Required as indicated, unless accomplished previously.\n\n\tTo prevent air leakage into the fuel feed lines within the wing tanks during fuel system suction feed operation at low fuel levels, accomplish the following:\n\n\t(a)\tPrior to the accumulation of either 20,000 flight hours or 7 years of age, or within 500 flight hours, whichever occurs later after March 12, 1984 (the effective date of Amendment 39-4803), institute an inspection program in accordance with Boeing Service Bulletin 737-28-1047, Revision 3, dated November 19, 1987, or earlier FAA-approved revisions.\n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.\n\n\t(d)\tThe inspection program instituted shall be in accordance with Boeing Service Bulletin 737-28-1047, Revision 3, dated November 19, 1987. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(e)\tThis amendment becomes effective on June 2, 1992.
2012-03-07: We are adopting a new airworthiness directive (AD) for certain Lycoming Engines reciprocating engines. This AD was prompted by a report of a "machined-from-billet'' HA-6 carburetor having a loose mixture control sleeve that rotated in the carburetor body causing restriction of fuel and power loss. This AD requires removing certain "machined-from-billet'' Volare LLC (formerly Precision Airmotive Corporation, formerly Facet Aerospace Products Company, formerly Marvel-Schebler (BorgWarner)) HA-6 carburetors, inspecting for a loose mixture control sleeve or for a sleeve that may become loose, repairing the carburetor, or replacing the carburetor with one eligible for installation. We are issuing this AD to prevent engine in-flight shutdown, power loss, and reduced control of the airplane.
2003-07-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757-200, 757-200CB, and 757-200PF series airplanes. This action requires repetitive detailed inspections to detect horizontal or vertical movement of the shims at the joint of the mid-bulkhead and the upper link fittings, and corrective action if necessary; or certain alternative actions that will terminate the requirement for the repetitive inspections. This action is necessary to detect and correct migration of shims at the joint of the mid-bulkhead and the upper link fittings, which could result in cracking of the strut and consequent loss of the strut and engine.
2012-03-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, and -300F series airplanes. This AD was prompted by reports of loss of avionics cooling due to an unserviceable relay installed on a panel as part of the cabin air conditioning and temperature control system (CACTCS). This AD requires doing certain wiring changes, installing a new relay and necessary wiring in the CACTCS, and performing an operational test of the cooling pack system. We are issuing this AD to prevent loss of electrical equipment bay cooling and the overheating of flight deck instruments, which would result in the eventual loss of primary flight displays, an unusually high pilot workload, and depressurization of the cabin.
2003-07-03: This amendment adopts a new airworthiness directive (AD) that applies to certain Twin Commander Aircraft Corporation (TCAC) Models 690D, 695A, and 695B airplanes. This AD requires you to initially inspect and modify and repetitively inspect areas of the wing and fuselage structure for fatigue damage and modify or replace any damaged parts. This AD is the result of tests that show that the service life of certain airplane parts cannot be reached unless an inspection and modification program (with any necessary replacements or modifications if fatigue damage is found) is incorporated. The actions specified by this AD are intended to detect and correct fatigue damage in the wing and fuselage areas without reducing the service life of the airplane. Such undetected and uncorrected damage could result in structural failure with consequent loss of control of the airplane.
96-18-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that requires an inspection to detect defects of the directional pilot valves (DPV); and replacement of any defective DPV with a new DPV, or deactivation of the thrust reverser system, if necessary. This amendment is prompted by a report indicating that, during a maintenance check, an uncommanded deployment and stowage of the thrust reverser occurred due to improperly modified DPV's. The actions specified by this AD are intended to prevent uncommanded deployment and stowage of the thrust reverser during maintenance activities, as a result of improperly modified DPV's, which could result in injury to maintenance personnel or other people on the ground.
98-15-26: This amendment supersedes an existing priority letter Airworthiness Directive (AD) 98-03-15, applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369, 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, 500N, 600N, and OH-6 helicopters that currently requires an inspection for main rotor blade (blade) cracks and for missing or cracked adhesive or paint. This amendment requires the same inspections required by the existing priority letter AD but deletes the Model 369 (Army YOH-6A), specifies recording torque events (TE), and establishes a shorter retirement life for certain blades. This amendment is prompted by an accident in which a blade failed on a Model 369D helicopter due to fatigue cracks. The actions specified by this AD are intended to detect cracks that could lead to failure of the blade and subsequent loss of control of the helicopter.
93-13-05: 93-13-05 DASSAULT AVIATION: Amendment 39-8618. Docket 92-NM-167-AD. Applicability: All Model Mystere-Falcon 900 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent interference with the operation of the engine controls and the flight controls, accomplish the following: (a) Within 50 hours time-in-service or 30 days after the effective date of this AD, whichever occurs first, accomplish paragraph (a)(1) or (a)(2) of this AD, as applicable. (1) For airplanes equipped with a Falcon Jet Corporation type interior (a water system pressure accumulator is installed on the left-hand side of frame 25): Perform a complete inspection of the water system in accordance with paragraph 13 of the Supplemental Maintenance Manual, Temporary Revision, dated February 1992; and install a placard, part number FGFB 825 003 760, in a visible location in the aft toilet compartment. (2) For airplanes equipped with a Dassault Aviation type interior (no water system pressure accumulator is installed at frame 25): Accomplish paragraphs (a)(2)(i), (a)(2)(ii), and (a)(2)(iii) of this AD. (i) Perform a complete inspection of the water system, in accordance with procedure 38-102 of the Maintenance Manual. (ii) Reinforce the sealing of the collector under the washbasin, in accordance with Dassault Aviation Service Bulletin F900-113 (F900-38-4), dated March 25, 1992. (iii) Perform an inspection of heating element 43 HR of pipe item 320, Illustrated Parts Catalog (IPC) 38-30-20, figure 10, in accordance with procedure 30-701 of the Maintenance Manual; and, if a discrepancy is found, replace the heating element within 50 hours time-in- service after performing the inspection required by this paragraph. (b) Prior to each flight of more than 4 hours time-in-service that occurs after accomplishing the requirements of paragraph (a) of this AD, accomplish the following, as applicable: Inspect the water system, in accordance with the paragraph entitled "Maintenance of Pressurized Central Water System" (page 19), of Revision 4 of the Supplemental Maintenance Manual (for Model Mystere-Falcon 900 series airplanes equipped with a Falcon Jet Corporation type interior); or in accordance with procedure 05-100 (temporary revision No. 59) of the Maintenance Manual (for Model Mystere-Falcon 900 series airplanes equipped with a Dassault Aviation type interior). (c) Within the next 300 hours time-in-service or 6 months after the effective date of this AD, whichever occurs first, repeat the inspection required by paragraph (a)(1) or (a)(2)(i) of this AD, as applicable. Thereafter, repeat the applicable inspection at intervals not to exceed 300 hours time-in-service or 6 months after the immediately preceding inspection, whichever occurs first. (d) Within 2 years after the effective date of this AD, modify the underfloor heating at frame 25, in accordancewith Dassault Aviation Service Bulletin F900-115 (F900-30-9), dated May 6, 1992, or Revision 1, dated February 25, 1993. (e) Accomplishment of modification of the underfloor heating in accordance with Dassault Aviation Service Bulletin F900-115 (F900-30-9), dated May 6, 1992, or Revision 1, dated February 25, 1993, constitutes terminating action for the inspections required by paragraphs (a), (b), and (c) of this AD. (f) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (g) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (h) The reinforcement shall be done in accordance with Dassault Aviation Service Bulletin F900-113 (F900-38-4), dated March 25, 1992. The modification shall be done in accordance with Dassault Aviation Service Bulletin F900-115 (F900-30-9), dated May 6, 1992; or Dassault Aviation Service Bulletin F900-115 (F900-30-9), Revision 1, dated February 25, 1993. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Falcon Jet Corporation, Customer Support Department, Teterboro Airport, Teterboro, New Jersey 07608. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 NorthCapitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on August 18, 1993.