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68-08-02: 68-08-02\tBOEING: Amdt. 39-590 as amended by Amendment 39-1516. Applies to Model 727 Series airplanes on which the aft trunnion extension has been chrome plated during overhaul. Compliance required as indicated. \n\n\tAn investigation of a recent failure of the aft trunnion extension of a Boeing Model 727 main landing gear outer cylinder (P/N 65-17651) indicates that the failure probably resulted from the use of an overhaul procedure which was not strictly in accordance with the sequence and techniques described by the Boeing Model 727 Overhaul Manual. Since this unsafe condition is likely to exist in other Boeing Model 727 Series airplanes, accomplish the following: \n\n\t1.\tWithin the next 75 hours time in service after April 12, 1968, unless already accomplished in accordance with superseded AD 68-07-06, or unless inspected in accordance with (3), inspect all chrome plated main landing gear outer cylinder aft trunnion extensions which have been overhauled in a manner other than specifically described by Section 32/12/1 of the Boeing 727 Overhaul Manual for any evidence of cracks. Inspect in areas and in the manner described in Boeing Alert Service Bulletin 32/153 dated March 29, 1968, or later FAA-approved revision. \n\n\t2.\tReinspect each affected main landing gear outer cylinder aft extension in the manner required by (1) at intervals not to exceed 800 landings. \n\n\t3.\tThe reinspections required by (2) can be discontinued for any outer cylinder aft extension which has been inspected and reworked in the manner described in Paragraph 4 of Boeing Telegraphic Revision 1 dated April 11, 1968, (or later FAA-approved revision) to Alert Service Bulletin No. 32/153, or in an equivalent manner approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t4.\tIf cracks are found, prior to further flight, replace the main landing gear outer cylinder with an unoverhauled cylinder or a cylinder which has been overhauled in the manner specifically describedby Section 32/12/1 of the Boeing Model 727 Overhaul Manual or a cylinder that has been inspected in accordance with (3). \n\n\t5.\tThe results of each initial inspection per (1) by a U. S. air carrier must be reported within three days to the assigned FAA inspector. \n\n\t6.\tFor the purpose of compliance with (2), subject to acceptance by the assigned FAA inspector, the number of landings may be determined by dividing each airplane's hours time in service since a landing gear outer cylinder was last replaced or inspected, by the operator's fleet average time from takeoff to landing for the airplane type. \n\n\t7.\tReplace all overhauled landing gear outer cylinders, which were not reworked in accordance with the provisions of this AD, within the next 1200 landings. \n\n\t8.\tThe reinspections required by (2) can be discontinued for any outer cylinder when those cylinders are replaced in accordance with (7). \n\n\tAmendment 39-590 became effective on publication in the Federal Register for allpersons except those to whom it was made effective immediately by telegram dated April 12, 1968. \n\n\tThis Amendment 39-1516 becomes effective upon publication in the Federal Register. \n\n\tThis Amendment (39-1516) supersedes Amendment 39-590 AD 68-07-06.
80-22-01: 80-22-01 MCDONNELL DOUGLAS: Amendment 39-3946. Applies to Model DC-8 series airplanes with 20,000 or more hours time in service, certificated in all categories. \n\n\tCompliance required as indicated unless already accomplished. To prevent crack growth which could result in structural failure of the wing lower skin and rear spar lower cap, accomplish the following: \n\n\t(a)\tVisually inspect the lower inboard aft wing skin panels and aft tang of the rear spar cap in the vicinity of the dihedral break at wing station Xcw=69.500 per the Phase 1 accomplishment instructions (Part 2) of McDonnell Douglas Service Bulletin 57-88 dated January 23, 1980, (hereinafter referred to as SB 57-88) within the times specified below: \n\n\nFor airplanes with total hours time\n in service on or after the effective\ndate of this AD.\nInspect within additional \nhours time in service from \nthe effective date of this AD. \n\n20,000 to 24,999\t\n900\n25,000 to 29,999\t\n700\n30,000 to 34,999\t\n500 \n35,000 and over\t\n300\n\t\n\t(b)\tModify Clip P/N 5649893-47 (Left Side) and -48 (Right Side) per SB57-88, Part 2, Accomplishment Instructions, Paragraph G within the compliance schedule specified in Paragraph (a) of this AD. \n\n\t(c)\tPrecoin ream the six holes in lower wing skin identified in SB57-88, Part 2.H per instructions of SB57-88, Part 2.H, Condition II, Paragraph 1, within the compliance schedule specified in Paragraph (a) of this AD. \n\n\t(d)\tReam five attachment holes identified in SB57-88 Part 2.H per instructions of SB57-88 Part 2.H Condition II, Paragraph 2, within the compliance schedule specified in Paragraph (a) of this AD. \n\n\t(e)\tInspect the eleven attachment holes identified in Paragraphs (c) and (d) of this AD for cracks in wing skin and rear spar lower cap aft tang using eddy current methods per SB 57-88, Part 2.H, Condition II, Paragraph 3, within the compliance schedule specified in Paragraph (a) of this AD. \n\n\t(f)\tIf cracks are found, as a result of the inspections of Paragraphs (a) or (e) of this AD, repair prior to further flight as indicated: \n\n\t\t1.\tIf cracks are less than 2.5 inches in length, rework in accordance with appropriate Condition of Service Sketch (SS) 3154, or Paragraph (f)(2) of this AD. Rework per SS 3154 requires repetitive inspections per Paragraphs (a) and (e) of this AD at intervals not to exceed: 1200 hours additional time in service since the last inspection for Conditions I and VI of SS 3154 or 1800 hours additional time in service for Conditions II through V of SS 3154, and repair within 3600 additional hours time in service subsequent to rework per Paragraph (f)(2) of this AD. \n\n\t\t2.\tRepair cracks which are 2.5 inches in length or greater, but less than 7.0 inches in length per SB57-88, Part 2.H, Condition I, Paragraph 3. \n\n\t\t3.\tRepair cracks which are 7.0 inches in length or greater after obtaining approval of the proposed repair from the Chief, Aircraft Engineering Division, FAA Western Region. Submit exactlocation and dimension of crack with the proposed repair. \n\n\t(g)\tIf no cracks are found as a result of inspections of Paragraphs (a) and (e) of this AD, coin six holes outboard of wing station Xcw=69.500 per SB57-88 Part 2.H, Condition II, Paragraph 4, and revert to repetitive inspection requirements of Paragraph (i) of this AD. \n\n\t(h)\tReturn the aircraft to serviceable condition per the appropriate instructions of SB57-88 prior to flight. \n\n\t(i)\tConduct repetitive visual inspections per Paragraph (a) and eddy-current inspection of the 11 attachment holes per Paragraph (e) at intervals not to exceed 3,600 hours time in service since the last such inspection. (Note: Do Not re-ream the eleven attachment holes inboard of station Xcw=69.500 after the initial inspection of Paragraph (e) of this AD.) \n\n\t(j)\tInstallation of the preventive modification per S/B 57-88, Part 2.H, Condition I, Paragraph 3, eliminates the requirement for repetitive inspections required by Paragraph (i) ofthis AD. \n\n\t(k)\tSpecial 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 required by this AD. \n\n\t(l)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective October 23, 1980.
2012-04-03: We are adopting a new airworthiness directive (AD) for BRP- Powertrain GmbH & Co KG Rotax 912 S2, 912 S3, and 914 F2 reciprocating engines. This AD requires performing a one-time inspection of the oil system for leaks and a torque check of the oil pump attachment bolts, and if leaks are detected, performing a one-time inspection of the oil pump and engine valve train, on certain serial number (S/N) BRP- Powertrain GmbH & Co KG Rotax 912 S2, 912 S3, and 914 F2 reciprocating engines. This AD was prompted by the discovery that during engine production, some engines may not have had the oil pump attachment bolts torqued to specification. We are issuing this AD to prevent oil leaks, [[Page 12451]] which could result in an in-flight engine shutdown and forced landing.
2012-03-52: We are adopting a new airworthiness directive (AD) for certain Mooney Aviation Company, Inc. (Mooney) Models M20R and M20TN airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires inspecting the tail pitch trim assembly for correct positioning and proper attachment and inspecting the Huck Bolt fasteners for proper security with repair as necessary. The AD also requires sending the inspection results to the FAA and Mooney. This AD was prompted by a report of an incident on a Mooney Model M20TN airplane regarding failure of the tail pitch trim assembly, which could result in loss of control. We are issuing this AD to correct the unsafe condition on these products.
97-21-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Teledyne Continental Motors E-165, E-185, E-225, O-470 and IO-470 series reciprocating engines. This action supersedes priority letter AD 97-15-01 that currently requires removal from service of affected cylinders, and reassembly with serviceable parts. This action adds the latest revision to applicable Critical Service Bulletin (CSB), corrects references to Parts of that CSB, and lists a new contact telephone number to obtain the CSB from the manufacturer. This amendment is prompted by the availability of the new CSB revision and the need to correct the CSB references. The actions specified by this AD are intended to prevent extreme side loading of the piston, and consequent failure of the piston and engine.
81-05-02: 81-05-02 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39-4048. Applies to all Model Falcon 10 airplanes certificated in all categories. Compliance required as indicated. To prevent overheating of the air conditioning system - freon compressor motor starting resistor and thus avoid the attendant potential fire hazard accomplish the following, unless already accomplished: Prior to May 1, 1981, remove the compressor motor starting resistor and thermostat, and install a time-delay device in the starting system in accordance with Avions Marcel Dassault- Breguet Aviation Service Bulletin No. F10 0177, dated December 5, 1978, or later FAA- approved revisions, or in a manner acceptable to the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the addresses listed above. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment supersedes AD 78-22-03. This amendment becomes effective March 2, 1981.
2012-03-08: We are superseding an existing airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), and CL-600- 2D24 (Regional Jet Series 900) airplanes. That AD currently requires repetitive detailed inspections for cracking or deformation, or pulled or missing fasteners, on the lower panel of the left- and right-hand main landing gear (MLG) doors, as applicable, and corrective actions if necessary. That AD also reduces the repetitive inspection interval for certain airplanes. This new AD adds a new modification of the MLG door configuration, and removes certain airplanes from the applicability. This AD was prompted by further analysis of the MLG door by the manufacturer. We are issuing this AD to prevent failure of the lower panel of the MLG door, departure of the lower panel from the airplane, and consequent damage to airplane structure, which could adversely affect the airplane's continuedsafe flight and landing.
97-18-06: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737 series airplanes, that requires revising the FAA-approved maintenance program to prohibit the use of pressure washing within the wheel well or on the landing gear and to prohibit the use of pumps and/or nozzles for washing wheel wells or the landing gear; or incorporation of a certain Temporary Revision to the Boeing Airplane Maintenance Manual into the FAA-approved maintenance program. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent corrosion of certain equipment due to the use of inappropriate pressure washing techniques. Corrosion of bearings, cables, electrical connectors, or other equipment in the main wheel well, if not detected and corrected in a timely manner, could result in reduced controllability of the airplane.
79-19-06: 79-19-06 CESSNA AIRCRAFT COMPANY: Amendment 39-3558. Applies to Cessna Model 210L, Model T210L, Serial Numbers 21061040 and subsequent, Model 210M, Model T210M and Model P210N series airplanes modified to incorporate Symbolic Displays, Inc. fuel flow indicating system per STC SA3835WE. Compliance required within 25 hours' time-in-service or thirty (30) days from the effective date of this AD, whichever occurs first, unless already accomplished. To prevent a possible fuel leak caused by the installation of Symbolic Displays, Inc. fuel flow indicating system per STC SA3835WE accomplish the following: (a) Inspect the fuel flow transducer installation on the upper left side of the engine near the fuel distributor manifold. (b) If a 4 inch long flexible hose (Aeroquip P/N AE7010001E0040 or Stratoflex P/N 111D417-4S-0040) is installed between the transducer and the fuel distributor, no further action is required per this AD. (c) If an NAS 424-4 coupling is installed between the fuel flow transducer and the fuel distributor, remove and replace the coupling with hose assembly Aeroquip Part Number AE7010001E0040 or hose assembly Part Number 111D417-4S-0040 (Stratoflex). NOTE: Symbolic Displays, Inc. Service Information Bulletin No. 72 dated June 15, 1979 and Installation Diagram Drawing No. 204724, Revision "B," pertain to this matter. (d) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective September 17, 1979.
2012-04-06: We are adopting a new airworthiness directive (AD) for all 328 Support Services GmbH (Type Certificate Previously Held by AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 airplanes. This proposed AD was prompted by several runway excursion incidents and a single accident where the power lever could not be operated as intended during the landing roll-out on Model Dornier 328-100 airplanes. This proposed AD would require a modification of the engine control box assembly. We are proposing this AD to prevent runway excursion, which could result in damage to the airplane and injury to the occupants.
97-20-14: This amendment adopts a new airworthiness directive (AD) that applies to all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU-2B series airplanes. This AD requires incorporating information into the Limitations Section of the Airplane Flight Manual (AFM) that would require pilot training before flight into known or forecast icing conditions after a certain date. This AD results from the Federal Aviation Administration's analysis that the current training level of the pilots-in-command (PIC) of the MU-2B series airplanes makes it difficult for pilots to recognize adverse operating conditions and operate safely while flying in icing conditions. Similar training to that required in this AD for pilots of other high performance airplanes has shown a lower accident rate over time after the training than before. The actions specified by this AD are intended to decrease the chance of icing-related incidents or accidents of the MU-2B series airplanes due to pilot error.
97-20-12: This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Systems (MDHS) Model MD-900 helicopters, that requires removing certain serial-numbered main rotor swashplate bearings (bearings) and replacing them with airworthy bearings. This amendment is prompted by reports that inspections of several helicopters revealed that the outer bearing race had been rotating relative to the swashplate assembly, which was evidenced by wear marks in the rotating swashplate. The actions specified by this AD are intended to prevent possible heat accumulation and resulting damage to the bearing caused by the bearing races rotating relative to the bearing seat, which could result in degraded helicopter response to pilot control input and possible loss of control of the helicopter.
2012-03-03: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.27 Mark 050 and F.28 Mark 0070 and 0100 airplanes. This AD was prompted by reports that the brightness of the tritium exit signs and lighting strips deteriorated below accepted levels. This AD requires a detailed inspection of tritium exit signs and emergency lighting strips, and replacement if necessary. We are issuing this AD to detect and correct insufficient brightness of the tritium exit signs and lighting strips, which could lead to an unsafe evacuation during an emergency, possibly resulting in injury to occupants. [[Page 12177]]
2012-02-15: We are superseding an existing airworthiness directive (AD) for certain Model 757-200, -200PF, -200CB, and -300 series airplanes. That AD currently requires inspecting certain power feeder wire bundles for damage, inspecting the support clamps for these wire bundles to determine whether the clamps are properly installed, and performing corrective actions if necessary. This new AD requires additional inspections for certain airplanes. This AD was prompted by a report that a power feeder wire bundle chafed against the number six auxiliary slat track, causing electrical wires in the bundle to arc, which damaged both the auxiliary slat track and power feeder wires. We are issuing this AD to prevent arcing that could be a possible ignition source for leaked flammable fluids, which could result in a fire. Arcing could also result in a loss of power from the generator connected to the power feeder wire bundle, and consequent loss of systems, which could reduce controllability of theairplane.
83-06-09: 83-06-09 WYTWORNIA SPRZETU KOMUNIKACYJNEGO, PZL-MIELEC: Amendment 39-4596. Applies to Model PZL M18 (Serial Nos. 1Z001-01 through 1Z001-05, 1Z001-08 through 1Z001-10, 1Z002-01 through 1Z002-05, 1Z003-01 through 1Z003-10, 1Z004- 01 through 1Z004-10, and 1Z005-01 through 1Z005-14) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. Within the next 50 hours time-in-service after the effective date of this AD accomplish the following: a) To prevent inflight engine shutdown due to unmonitored fuel transfer between tanks, install non-return (check) valves Part Number (P/N) D61.170.00.G, install a second fuel quantity gauge, P/N 64126 or 6246-8, and install fuel filler placards in accordance with procedures III. A., III. B., and III. H. of Mandatory Bulletin I/009/81 and ERRATA sheet. NOTE: The modifications required by paragraph a) have been accomplished by the manufacturer on aircraft Serial Numbers 1Z001-02, 1Z004-02, 1Z004-05, 1Z004-06, and 1Z004- 10. b) To eliminate mechanical linkage interference in the power controls, inspect the support tube (P/N D65.250.00.2) installation to assure that the propeller governor push rod to carburetor orifice and carburetor (R.P.M.) adjustment levers clearance is as prescribed in procedures III. D. of Mandatory Bulletin I/009/81. If clearance is insufficient, readjust support tube and modify the carburetor orifice as prescribed to meet the clearances specified in procedures III. D. c) To eliminate a possible source of head injury to the pilot during a hard landing, replace the sunlight filter position adjustment butterfly nut, P/N 1414s49-8-ka, with ball knob P/N D74.280.00.0 as prescribed in procedures III. F. of Mandatory Bulletin I/009/81. d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. e) 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, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 4, 1983.
96-12-03 R1: This document corrects the airworthiness directive (AD) number of an amendment that was published in the Federal Register on August 22, 1997 (62 FR 44535), and concerns Aviat Aircraft, Inc. Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B airplanes. The referenced amendment revises AD 96-12-03, but was inadvertently assigned the number of AD 97-17-07 instead of AD 96-12-03 R1. The AD currently requires repetitively inspecting the aft lower fuselage wing attach fitting on both wings for cracks and modifying any cracked aft lower fuselage wing attach fitting. Modifying the aft lower fuselage wing attach fitting on both wings eliminates the repetitive inspection requirement of the AD. This action corrects the amendment to reflect the right AD number throughout the entire document.
2012-04-05: We are superseding an existing airworthiness directive (AD) for all GE CF6-80C2B series turbofan engines. That AD currently requires installing software version 8.2.Q1 to the engine electronic control unit (ECU), which increases the engine's margin to flameout. This new AD requires the removal of the affected ECUs from service. This AD was prompted by two reports of engine flameout events during flight in inclement weather conditions, eight reports of engine in- flight shutdown (IFSD) events caused by dual-channel central processing unit (CPU) faults in the ECU, and four reports of engine flameout ground events. We are issuing this AD to prevent engine flameout or un- commanded engine IFSD of one or more engines, leading to an emergency or forced landing of the airplane.
97-20-11: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Model TBM 700 airplanes. This AD requires removing the main landing gear (MLG) inboard doors and the door locking control mechanism (MOD 70- 065-32). This AD is the result of an incident on one of the affected airplanes where the MLG inboard door locking hooks (hinges) corroded, caused the doors to jam, and prevented the MLG from extending. The Federal Aviation Administration's analysis reveals that removing the MLG inboard doors will not cause any airplane safety or performance problems. The actions specified by this AD are intended to prevent the MLG from failing to extend because of corroded MLG inboard locking hinges, which could result in loss of control of the airplane during landing operations.
60-22-01: 60-22-01 LAKE (COLONIAL): Amdt. 213 Part 507 Federal Register October 29, 1960. Applies to Colonial C-2 Serial Numbers 115, 121, 126 and Subsequent. Lake Serial Numbers 244 and 245. Compliance required within 100 hours' time in service after effective date of this amendment. Due to several failures of the engine mount bolts, the following shall be accomplished: (a) Replace AN 7-35 engine-to-engine mount bolts with MS 20007-48 or NAS 464- 7L-51 strength bolts or equivalent (4 places). (b) Replace Lord Mounts P/N J-7402-1 with Lord Mounts P/N J-7402-5 or -6, or equivalent (4 places). (Lake Service Bulletin Number 2 covers this same subject.) This directive effective November 29, 1960.
2012-03-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a report of deformation at the neck of the pressure regulator body on certain oxygen cylinder and regulator assemblies (CRA). This AD requires an inspection to determine if a certain oxygen CRA is installed and the replacement of oxygen CRAs containing pressure regulators having a certain part number. We are issuing this AD to prevent elongation of the pressure regulator neck, which could result in rupture of the oxygen cylinder, and in the case of cabin depressurization, oxygen not being available when required.
97-20-03: This amendment adopts a new airworthiness directive (AD), applicable to all de Havilland Model DHC-7 series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit positioning of the power levers below the flight idle stop during flight, and to add a statement of the consequences of such positioning of the power levers. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller ground beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop when the airplane is in flight.
97-20-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all Lockheed Model L-188A and L-188C series airplanes. This amendment requires revising the Airplane Flight Manual (AFM) to prohibit the positioning of the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below flight idle stop. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines where the propeller ground beta was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
97-19-14: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney JT8D series turbofan engines, that currently requires inspections of low pressure turbine (LPT) blade sets for blade shroud crossnotch wear, and removal, if necessary. In addition, the current AD requires, as a terminating action to the inspections, installation of improved LPT containment hardware, and installation of an improved No. 6 bearing scavenge pump bracket bushing. This amendment keeps the compliance actions of the current AD intact but changes the compliance time for LPT containment hardware installation from the current calendar end-date to December 31, 1998, for engines that contain suspect 4th stage hubs identified by serial number. This amendment is prompted by a report of a fourth stage hub manufacturing defect that led to the failure of the hub and subsequent release of LPT blades. The actions specified by this AD are intended to prevent damage to the aircraftresulting from engine debris following an LPT blade, shaft, or hub failure. The incorporation by reference of PW Alert Service Bulletin No. A6131, Revision 1, dated May 16, 1995; PW Alert Service Bulletin No. A6131, Revision 2, dated July 28, 1997; PW Alert Service Bulletin No. A6274, Original, dated November 7, 1996; and PW Alert Service Bulletin No. A6274, Revision 1, dated December 9, 1996, is approved by the Director of the Federal Register as of October 24, 1997. The incorporation by reference of all other publications listed in the regulations was previously approved as of November 14, 1994 (59 FR 51842).
97-19-15: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 767 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to include procedures that will ensure that the center tank fuel pumps are not operated with less than 1,000 pounds of fuel in the center tank. This amendment is prompted by a report indicating that a fuel pump failed due to damage to an impeller unit and pumping unit housing caused by a loose diffuser ring in the fuel pump assembly. The actions specified in this AD are intended to ensure the flight crew is advised of procedures that will ensure that the center tank fuel pumps are not operated with less than 1,000 pounds of fuel, which will prevent ignition of fuel vapors due to the generation of sparks and a potential ignition source inside the fuel tank caused by metal-to- metal contact during dry fuel pump operation.
85-17-04: 85-17-04 EMPRESA BRASILEIRA DE AERONAUTICA S.A. (EMBRAER): Amendment 39-5126. Applies to Models EMB-110P1 and EMB-110P2 (all serial numbers) airplanes certificated in any category which have aluminum elevator control rod tubes installed. Compliance: Required as indicated, unless already accomplished. To prevent failure of the elevator control rod tube, accomplish the following: (a) Within the next 50 hours time-in-service after the effective date of this AD, visually inspect the elevator control rod tubes, P/N 4A-500-10-09-01, for evidence of corrosion or cracks. If corrosion or cracks are found, prior to further flight replace the control rod tube in accordance with Embraer Service Bulletin (S/B) No. 110-27-076, Revision 01, dated July 2, 1985. (b) Within 150 hours time-in-service or 30 (thirty) days, whichever occurs first, after the effective date of this AD, replace both left and right elevator aluminum control rod tubes P/N 4A-500-10-09-01 with steel control rod tubes P/N 110-500-10-00-04-01. Reidentify the elevator control rod assembly with the new P/N 110-500-10-00-09. (c) Airplanes may be flown in accordance with Federal Aviation Regulation 21.197 to a location where the AD may be accomplished. (d) An equivalent method of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, FAA, 1075 Inner Loop Road, College Park, Georgia 30337; Telephone (404) 763-7428. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Embraer, Post Office Box 343 - CEP 12.200 Sao Jose Dos Campos, Sao Paulo, Brazil, or FAA, Office of Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on August 30, 1985.