Results
75-26-13: 75-26-13 HAWKER SIDDELEY AVIATION: Amendment 39-2469. Applies to DH-125 series 3AR, S/N 25/148 and 149; series 3ARA, S/N 25/151, 152, 153, 155, 156, 158, 159, and NA 700 through NA 710; series 400 A, S/N NA 711 through NA 752 airplanes and to BH-125 series 400 A, S/N NA 753 through NA 780; and series 600A, S/N 25/6001 through 6004, 6007, 6009, 6010, 6011, 6013, 6014, 6016, 6018, 6020, 6022 through 6026, 6032, 6034, 6038, 6040, 6044, 6046, 6047, and 6051 airplanes. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent structural damage to the inboard end of the flaps which can result from landing on heavily watered, or slush, or snow covered runways, incorporate the structural modification to the inboard end of the flap (L/H & R/H) in accordance with the accomplishment instructions in Hawker Siddeley Aviation Ltd. Service Bulletin 27-112 (2426), Revision 1, dated March 11, 1975, or an FAA-approved equivalent. This amendment becomes effective on January 15, 1976.
2000-18-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A300-600, and A310 series airplanes, that requires replacement of the transformer rectifier units (TRU) in the avionics compartment with new, improved TRU's. 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 failure of the TRU's. Failure of multiple TRU's could result in loss of the thrust reversers, autothrottle, flaps, and various systems (wing/cockpit window anti-ice, trim tank pumps, and windshield wipers) on the airplane; or incorrect information displayed to the flight crew.
95-12-01: This amendment supersedes Airworthiness Directive (AD) 93-21-12, which currently requires inspecting (one-time visual and dye penetrant) the wing forward spar fuselage attachment assembly for cracks or corrosion on certain Piper Aircraft Corporation (Piper) PA-25 series airplanes, and replacing or repairing any cracked or corroded part. This action requires repetitively inspecting (using ultrasonic and dye penetrant procedures) the wing forward spar fuselage attachment assembly for cracks or corrosion, replacing or repairing any cracked or corroded part, and reporting to the Federal Aviation Administration (FAA) the results of the inspections. This action is prompted by the FAA's lack of confidence in detecting internal corrosion in the wing forward spar fuselage attachment fittings while accomplishing the inspection methods required by AD 93-21-12. A report of a crack in the wing forward spar fuselage attachment assembly on an airplane where the inspection requirements ofAD 93-21-12 were accomplished also prompted this action. The actions specified by this AD are intended to prevent possible in-flight separation of the wing from the airplane caused by a cracked or corroded wing forward spar fuselage attachment assembly.
2013-19-07: We are adopting a new airworthiness directive (AD) for Eurocopter Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, EC155B1, AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters with certain EADS Sogerma pilot and co-pilot seats installed. This AD requires inspecting the rear beam of [[Page 60682]] each seat to determine if all of the weld beads are present and replacing the seat if any weld bead is missing. This AD is prompted by a maintenance inspection that discovered a missing weld bead on the rear beam of a pilot seat. These actions are intended to prevent failure of the pilot and co-pilot seats and subsequent injury to the pilot or co-pilot.
2013-19-19: We are adopting a new airworthiness directive (AD) for Eurocopter Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD requires replacing certain serial-numbered main gearbox (MGB) bevel gear vertical shafts because they are no longer airworthy. Also, this AD requires certain inspections of each MGB bevel gear vertical shaft (shaft) for a crack. Also, this AD requires if there is a crack, replacing the shaft with an airworthy part before further flight. This AD is prompted by two incidents of emergency ditching after warning indications of loss of MGB oil pressure. These actions are intended to detect a cracked shaft, which could result in loss of MGB oil pressure, loss of the MGB lubrication system, and subsequent loss of control of the helicopter.
94-17-14: This amendment supersedes an existing airworthiness directive (AD), applicable to British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that currently requires replacing the quick release coupling halves on each end of the pump case drain line on the hydraulic engine driven pump (EDP) on the number 2 and number 3 engines with improved fire resistant coupling halves. This amendment revises the applicability of the existing AD. This amendment is prompted by the identification of additional airplanes that are subject to the addressed unsafe condition. The actions specified by this AD are intended to prevent hydraulic fluid leakage from the pump case drain line quick release coupling, which could fuel the flames in the event of an engine fire.
2000-18-04: This amendment adopts a new airworthiness directive (AD) that applies to Aviointeriors S.p.A. (formerly ALVEN), Seat Model 312. This AD requires initial and repetitive inspections of the seat center crossmember for cracks, and if necessary, replacing the crossmember with a new crossmember. This amendment is prompted by reports of cracks in the crossmember that were found during normal maintenance. The FAA is issuing this AD to prevent the loss of the structural integrity of the seat due to cracks in the seat center crossmember.
2013-19-06: We are adopting a new airworthiness directive (AD) for Robinson Model R22, R22 Alpha, R22 Beta, and R22 Mariner helicopters with certain fuel shut-off valves installed. This AD requires replacing the fuel shut-off valve with a newer design fuel shut-off valve. This AD is prompted by three accidents that occurred because the fuel shut- off valve was inadvertently moved to the ``off'' position. These actions are intended to prevent inadvertent closing of the fuel valve, which could result in engine power loss from which a safe landing may not be possible.
2013-19-05: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (Bell), Model 214B, 214B-1, and 214ST helicopters. This AD requires creating a component history card or equivalent record for certain pylon support spindle assemblies (spindles), establishes a new retirement life for spindles installed on Model 214B and 214B-1 helicopters, reduces the retirement life for spindles installed on Model 214ST helicopters, and requires replacing any spindle that has reached its airworthiness retirement life. This AD was prompted by three in-flight failures of the spindle that resulted in forced landings. The actions of this AD are intended to prevent failure of a spindle and subsequent loss of control of the helicopter.
75-07-10: 75-07-10 AIRESEARCH MANUFACTURING COMPANY of ARIZONA: Amendment 39-2144 as amended by Amendment 39-2189. Applies to AiResearch TFE731-2 and -3 series engines. Compliance required as indicated. To detect, prevent and correct wear of the transfer gearbox vertical bevel gear bearing support which can result in failure of the accessory drive and contamination of the engine lubrication system, accomplish the following: (A) Within the next 25 hours time in service after receipt of this Airworthiness Directive, unless previously accomplished, and at intervals not to exceed 50 hours time in service thereafter, inspect the lower shoulder of transfer gearbox vertical bearing support for wear and replacements as required per AiResearch Service Bulletin TFE731-72-3019, dated February 27, 1975, or later FAA-approved revisions. (B) The inspections required by paragraph (A) above, are not required if the engine is equipped with a transfer gearbox assembly, P/N 3070093-3, designated as Series I, Change 2 or Series 3, and may be discontinued on engines equipped with Series I Transfer Gearbox Assemblies when the bearing support, P/N 3070217-1, is replaced with an improved bearing support, P/N 3070217-3, per AiResearch Service Bulletin TFE731-72-3020, dated February 27, 1975, or later FAA-approved revisions. Bearing supports, P/N 3070217-1, which are removed from service shall be rendered unserviceable. (C) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiating data. (D) Aircraft may be flown to a base for performance of maintenance required by this AD per FAR's 21.197 and 21.199. Amendment 39-2144 became effective April 3, 1975, for all persons except those to whom it was made effective by airmail letters dated February 28, 1975. This amendment 39-2189 becomes effective May 1, 1975.
92-04-09: 92-04-09 TELEDYNE CONTINENTAL MOTORS: Amendment 39-8585. Docket 93-ANE-24. Applicability: Teledyne Continental Motors (TCM) IO-360 series, TSIO-360 series, and LTSIO-360 series reciprocating engines, identified by model and serial number in TCM Service Bulletin (SB) No. M92-4, Revision 1, dated February 5, 1992, and all other TCM IO-360 series, TSIO-360 series, LTSIO-360 series, and Rolls- Royce Motors Model TSIO-360 series reciprocating engines, installed on but not limited to Cessna 337, T337, and P337 series; Cessna 172XP; Mooney M20K; Piper PA34-200T, PA34-220T, PA28R-201T and PA28RT- 201T airplanes. Compliance: Required prior to further flight, unless accomplished previously. To prevent engine failure caused by failure of the rocker shaft hold down stud, accomplish the following: (a) For engines that have the rocker arm shaft hold down stud nut torqued in accordance with TCM SB No. M92-4, dated January 10, 1992, and are in compliance with AD 92-02-20 or AD 92-02-20R1, retorque the rocker arm shaft hold down stud nut to 110-120 inch pounds in accordance with TCM SB M92-4, Revision 1, dated February 5, 1992. (b) For engines listed by model and serial number in TCM SB No. M92-4, Revision 1, dated February 5, 1992, inspect, and if necessary, rework cylinder assembly, in accordance with TCM SB No. M92-4, Revision 1, dated February 5, 1992. (c) For Rolls-Royce Motors engines and all other engines containing cylinder assemblies, with cylinder assembly dates between June 1991 through December 1991, and identified by TCM Part Numbers 646924, 649484, 652955, or 653098, and all "A" suffix numbers of these base part numbers, inspect, and if necessary, rework, in accordance with TCM SB No. M92-4, Revision 1, dated February 5, 1992. NOTE: Cylinder assembly dates are stamped on the cylinder head between the two rocker shaft pockets. (d) Uninstalled cylinder assemblies, with cylinder assembly dates between June 1991 and December 1991, and identifiedby TCM Part Numbers 646924, 649484, 652955, 653098, and all "A" suffix numbers of these base part numbers, shall not be placed in service unless inspected or reworked in accordance with TCM SB No. M92-4, Revision 1, dated February 5, 1992. (e) After accomplishment of the requirements of paragraphs (a), (b), (c), or (d) of this AD, as applicable, mark with VIBRO-ETCH or other similar device the letter "B" adjacent to the cylinder assembly date on the cylinder head between the two rocker shaft pockets. (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, Atlanta Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Atlanta Aircraft Certification Office. (g) The retorquing, inspections, and rework shall be done in accordance with the following service bulletin: Document No. Pages Revision Date TCM SB No. M92-4 1-2 1 February 5, 1992 Total pages: 2. 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 Teledyne Continental Motors, P.O. Box 90, Mobile, AL 36601. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment supersedes priority letter AD 92-02-20 R1, issued January 24, 1992. (i) This amendment becomes effective June 22, 1993, to all persons except those persons to whom it was made immediatelyeffective by priority letter AD 92-04-09, issued February 18, 1992, which contained the requirements of this amendment.
2013-19-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by a \n\n((Page 59802)) \n\nreport of cracks found in the skin at body station (STA) 540 just below stringer S-22L on a Model 737-700 series airplane. This AD requires repetitive detailed and high frequency eddy current inspections for cracking of the skin around the eight fasteners common to the ends of the STA 540 bulkhead chords between stringers S-22 and S-23, left and right sides; and corrective actions and preventive modification if necessary. We are issuing this AD to detect and correct fatigue cracking in the skin, which can result in rapid decompression of the cabin.
67-23-02: 67-23-02\tBOEING: Amdt. 39-462, Part 39, Federal Register August 11, 1967. Applies to Model 707 and 720 Series Airplanes, except 707-300B and -300C Series. \n\n\tCompliance required within the next 7,000 hours' time in service after the effective date of this AD unless already accomplished. \n\n\tTo prevent explosion of fuel vapors in the fuel tanks as a result of lightning-induced ignition at the fuel tank vent outlet, accomplish one of the following, or an equivalent, approved by the Chief, Aircraft Engineering Division, FAA Western Region \n\n\t(a)\tInstall a flame and explosion suppression system in the fuel tank vent outlet system to prevent flame propagation through the vent system following ignition of vapor by lightning at the vent outlet; or \n\n\t(b)\tInstall an auxiliary vent tube with flame arrester, to the vent system surge tank to provide, during flight, continuous airflow inward through the existing outlet and outward through the protected auxiliary tube. \n\n\tThis amendmenteffective September 10, 1967.
93-15-01: 93-15-01 FAIRCHILD AIRCRAFT: Amendment 39-8647. Docket No. 93-CE-20-AD. Supersedes AD 92-16-11, Amendment 39-8320. Applicability: The following model and serial number airplanes, certificated in any category: Model Serial Numbers SA226-T T201 through T275 and T277 through T291 SA226-T(B) T(B)276 and T(B)292 through T(B)417 SA226-AT AT001 through AT074 SA226-TC TC201 through TC419 SA227-TT TT421 through TT541 SA227-AT AT423 through AT695 SA227-AC AC406, AC415, and AC416 SA227-AC AC420 through AC783, and AC785 SA227-BC BC420 through BC783, and BC785 Compliance: Required initially upon the accumulation of 10,000 hours time-in-service (TIS) or within the next 1,000 hours TIS after the effective date of this AD, whichever occurs later, unless already accomplished (see NOTE 1), and thereafter as indicated. NOTE 1: Compliance with superseded AD 92-16-11 is considered "unless already accomplished" for the initial inspection and modification requirements of this AD except as specified in paragraph (c) of this AD. To prevent failure of the horizontal stabilizer caused by broken pivot fitting fasteners, which could result in loss of control of the airplane, accomplish the following: (a) Modify the horizontal stabilizer aft spar attach fitting installation in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Service Bulletin (SB) 226-55-010, Horizontal Stabilizer Fitting Fasteners, Issued: May 13, 1991; Revised: December 13, 1991, or Fairchild SB 227-55-006, Horizontal Stabilizer Fitting Fasteners, Issued: May 13, 1991; Revised: January 20, 1993, as applicable. (b) Modify the stabilizer skin in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Fairchild SB 226-55-010, Horizontal Stabilizer Fitting Fasteners, Issued: May 13, 1991; Revised: December 13, 1991, or Fairchild SB 227-55-006, Horizontal Stabilizer Fitting Fasteners, Issued: May 13, 1991; Revised: January 20, 1993, as applicable. (c) If any Model SA227-AC or SA227-BC airplane incorporating any serial number of AC528 through AC783, AC785, BC528 through BC783, or BC785 has been modified as required by AD 92-16-11 in accordance with Fairchild SB 227-55-006, Horizontal Stabilizer Fitting Fasteners, Issued: May 13, 1991; Revised: May 22, 1991, then the only modification required by paragraphs (a) and (b) of this AD is that which is specified in paragraph B (3) of the ACCOMPLISHMENT INSTRUCTIONS section of Fairchild SB 227-55-006, Horizontal Stabilizer Fitting Fasteners, Issued: May 13, 1991; Revised: January 20, 1993. (d) Visually inspect the radius area of the rib splice strap for cracks in accordance with Figure 2 of Fairchild SB 226-55-010, Horizontal Stabilizer Fitting Fasteners, Issued: May 13, 1991; Revised: December 13, 1991, or Figure 3 of Fairchild SB 227-55-006, Horizontal Stabilizer Fitting Fasteners, Issued: May 13, 1991; Revised: January 20, 1993, as applicable. (i) If cracks arefound, prior to further flight, repair in accordance with a scheme obtained from the manufacturer through the Fort Worth Airplane Certification Office at the address specified in paragraph (f) of this AD, and reinspect thereafter at intervals not to exceed 5,000 hours TIS. (ii) If no cracks are found, reinspect thereafter at intervals not to exceed 5,000 hours TIS. (e) 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. (f) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, FAA, 4400 Blue Mound Road, Fort Worth, Texas 76193-0150. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Certification Office.NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth Airplane Certification Office. (g) The inspections and modifications required by this AD shall be done in accordance with Fairchild Service Bulletin 226-55-010, Horizontal Stabilizer Fitting Fasteners, Issued: May 13, 1991; Revised: December 13, 1991, or Fairchild Service Bulletin 227-55-006, Horizontal Stabilizer Fitting Fasteners, Issued: May 13, 1991; Revised: January 20, 1993, as applicable. 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 Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment (39-8647) supersedes AD 92-16-11, Amendment 39-8320. (i) This amendment becomes effective on September 16, 1993.
92-19-03: 92-19-03 AIRBUS INDUSTRIE: Amendment 39-8361. Docket No. 92-NM-35-AD. Applicability: Model A300, A310, and A300-600 series airplanes, on which Modification 4803 has not been accomplished, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the ram air turbine (RAT) to release properly, accomplish the following: (a) Within 6 months after the effective date of this AD, conduct a test of the RAT Teleflex flexible control cables to verify that the control cables operate properly (the load to move the handle must be equal to or lower than 5.5 daN), in accordance with Airbus Industrie Service Bulletins A300-29-097, Revision 2, dated August 27, 1991 (for Model A300 series airplanes); A310-29-2030, Revision 2, dated August 27, 1991 (for Model A310 series airplanes); or A300-29-6022, Revision 2, dated August 27, 1991 (for Model A300-600 series airplanes), as applicable. (b) If no discrepancy is detected, thereafter at intervals not to exceed 30 months, accomplish the "Maintenance Task" specified in paragraph 2.C. of Airbus Industrie Service Bulletin A300-29-097, Revision 2, dated August 27, 1991 (for Model A300 series airplanes); A310-29-2030, Revision 2, dated August 27, 1991 (for Model A310 series airplanes); or A300-29-6022, Revision 2, dated August 27, 1991 (for Model A300-600 series airplanes); as applicable. (c) If any discrepancy is detected (e.g., the load to move the handle during operation of the left or right control cable is higher than 5.5 daN), accomplish paragraphs (c)(1) and (c)(2) of this AD: (1) Prior to further flight, accomplish the "Maintenance Task" specified in paragraph 2.C. of Airbus Industrie Service Bulletin A300-29-097, Revision 2, dated August 27, 1991 (for Model A300 series airplanes); A310-29-2030, Revision 2, dated August 27, 1991 (for Model A310 series airplanes); or A300-29-6022, Revision 2, dated August 27, 1991 (for Model A300-600 series airplanes), as applicable. (2) At intervals not to exceed 30 months after the accomplishment of the Maintenance Task in accordance with paragraph (c)(1) of this AD, repeat the Maintenance Task in accordance with the applicable Airbus Industrie service bulletin. (d) Modification of the Teleflex flexible control cable on the RAT, in accordance with Airbus Industrie Service Bulletin A300-29-0099, dated January 30, 1992 (for Model A300 series airplanes), A310-29-2032, Revision 1, dated June 10, 1992 (for Model A310 series airplanes), or A300-29-6024, Revision 1, dated June 10, 1992 (for Model A300-600 series airplanes), as applicable, constitutes terminating action for accomplishing the repetitive "Maintenance Tasks" required by paragraphs (b) and (c)(2) of this AD. (e) 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, TransportAirplane 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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (f) 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. (g) The test, "Maintenance Tasks," and modification shall be done in accordance with the following Airbus Industrie service bulletins, as applicable, which contain the specified effective pages: Service Bulletin Referenced Page Number Revision Level Shown on Page Date Shown on Page A310-29-2030, Revision 2, 1-15 2 August 27, 1991 A300-29-6022 Revision 2, August 27, 1991 1-13 2 August 27, 1991 A300-29-097, Revision 2,August 27, 1991 1, 4-17 2 3 2 Original 1 August 27, 1991 June 3, 1991 A300-29-6024, Revision 1, June 10, 1992 1, 3-17 2 1 Original June 10, 1992 January 30, 1992 A310-29-2032, Revision 1, June 10, 1992 1, 4-19 2-3 1 Original June 10, 1992 January 30, 1992 A300-29-0099, January 30, 1992 1-19 Original January 30, 1992 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. 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 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on November 20, 1992.
2025-06-02: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by a report of a 5-inch crack on the upper wing skin at a certain wing station of the right wing. This AD requires repetitive inspections for cracking of the upper wing skin common to certain fasteners and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2021-18-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-171N; Model A320-271N, -272N, and -273N \n\n((Page 48297)) \n\nairplanes; and Model A321-271N, -272N, -271NX, and -272NX airplanes. This AD was prompted by a report indicating that during inspection of the engines, two original rods installed to maintain an interface plate between the pylon and nacelle were found damaged at both rod-eye ends. This AD requires repetitive inspections of the pylon/engine interface rods for damage, and applicable corrective actions, and limits the installation of affected parts under certain conditions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2003-12-03: This amendment adopts a new airworthiness directive (AD), applicable to all Israel Aircraft Industries, Ltd., Model 1124 and 1124A series airplanes, that requires revising the airplane flight manual to advise the flightcrew to don oxygen masks as a first and immediate step following a cabin altitude alert. This action is necessary to prevent incapacitation of the flightcrew due to lack of oxygen. This action is intended to address the identified unsafe condition.
76-14-06: 76-14-06 BOEING: Amendment 39-2664. Applies to all Boeing 747 series airplanes certificated in all categories. Compliance required as indicated. \n\tWithin 20 days after the effective date of this Airworthiness Directive, accomplish the following: \n\t1.\tInspect the dry bay areas between the outboard reserve tanks, wing station 1280, and the surge tanks, wing station 1485, for evidence of fuel leaks, unless already accomplished per Boeing service letter 747-SL-28-3 dated June 11, 1976. Verify the existence of a clear drain path through each vent/drain hole and stringer limber hole to prevent accumulation of fluids. Repair leaks per Boeing 747 Maintenance Manual Chapter 28-11-00, Figure 802. Aircraft exhibiting leakage rates exceeding Maintenance Manual limits must be repaired before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. Clean all dry bay access door clamp rings and wing skin mating surfaces. Tighten all attach bolts to 35-40 inch-pounds of torque. This inspection is not required on 747-SP airplanes with active 2 and 3 reserve tanks and 747-200 airplanes with auxiliary fuel tanks. \n\t2.\tUnless already accomplished per Boeing service letter 747-SL-28-4 dated June 21, 1976, inspect all engine struts for evidence of fuel leakage. Inspections shall be accomplished by gaining access on the left side of each nacelle strut through the B, C, and D panels with prefix numbers 452, 462, 472, or 482. Repair all fuel leaks per Boeing Maintenance Manual Chapter 28-22-07 before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. \n\t3.\tUnless already accomplished per Boeing service letter 747-SL-28-5 dated June 21, 1976, inspect overwing fuel filler caps for approved part numbers 10-3297-119 (GABB P/N 38222-2) or 10-3297-147 (GABB P/N 38222-3) and determine that non-metallic lanyards are installed, or provide corrective action in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Northwest Region.\n \tReport all findings to the Chief, Engineering and Manufacturing Branch, FAA, Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108 through the assigned FAA principal maintenance inspector. The report must include the following: \n\t(1)\tAirplane serial number. \n\t(2)\tAirplane total time. \n\t(3)\tDescription of condition and location of leaks. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174). \n\tThe 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)(i). \n\tAll persons affected by this directive who have not already received these documents may obtain copies by request to the Boeing Company, P. O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA, Northwest Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated June 25, 1976.
75-24-03: 75-24-03 LEARJET MODEL 24A: Amendment 39-2423. Applies only to airplanes modified per STC ST7RM when used in cargo operation. Compliance required within the next 150 hours time in service after the effective date of this AD, unless already accomplished. To provide an adequate emergency exit for flight crew members, install Alpine Aircraft Charters, Inc., STC SA14RM or equivalent approved by Chief, Engineering and Manufacturing Branch, Rocky Mountain Region, or provide access to the existing emergency exit on the right side of the fuselage in a manner approved by Chief, Engineering and Manufacturing Branch, Rocky Mountain Region. This amendment becomes effective on December 18, 1975.
2013-19-10: We are adopting a new airworthiness directive (AD) for PILATUS AIRCRAFT LTD. Model PC-12/47E airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as common grounding of both the pilot primary flight display (PFD) and the Electronic Standby Instrument System (ESIS). If the common ground fails both navigations systems could fail simultaneously, which could result in loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
2013-16-21: We are superseding an airworthiness directive (AD) for Agusta Model A109E helicopters that required reducing the tail rotor (T/R) blade life limit, modifying a T/R hub and grip assembly, re-identifying two T/R assemblies, clarifying the never-exceed speed (Vne) limitation, and reducing the inspection interval. Since we issued that AD, the manufacturer has redesigned a T/R grip bushing (bushing) that reduces the loads, which caused the T/R cracking, on the T/R blades. This action requires installing the new bushing and re-identifying the T/R hub-and-grip and hub-and-blade assemblies and requires a recurring inspection of each bushing. These actions are intended to prevent fatigue failure of a T/R blade and subsequent loss of control of the helicopter.
73-26-08: 73-26-08 BEECH: Amendment 39-1764. Applies to Models 95-55, 95-A55, 95-B55 (Serial Numbers TC-1 through TC-1573 except TC-350); 95-C55, D55, D55A, E55 and E55A (Serial Numbers TE-1 through TE-919 and TC-350), airplanes equipped with the EDO-AIRE Mitchell AK-292 Autopilot. \n\n\tCompliance: Required within 25 hours' time in service after the effective date of this AD, unless previously accomplished in accordance with data described herein or any alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tTo determine if the roll and pitch servo clamps have slipped and to assure sufficient torque on the clamp bolts accomplish the following: \n\n\tA)\tInspect the roll pitch bridle cables and clamps by: \n\n\t\t(1)\tRunning the aileron and pitch controls through their full travel to assure that there is no binding or restrictions between the bridle cables and clamps and aircraft components. Clamps should be positioned so there is no binding or restriction between the bridle cable and capstan flange. \n\n\t\t(2)\tDetermine that the bridle cables tensions are the same as the tension of the control cable they are attached to. \n\n\tB)\tTorque the bolts on the cable clamps to 55 + or - 5 in. lbs. with a minimum gap of .005 between halves of clamp after torquing. \n\n\tNOTE: Figure 1, attached hereto, depicts a typical installation of the bridle cables and clamps. \n\n\tThis amendment becomes effective December 26, 1973.
92-10-09: 92-10-09 BRITISH AEROSPACE: Amendment 39-8243. Docket No. 91-NM-260-AD. Applicability: British Aerospace Model BAe 125-800A series airplanes, having NA numbers as listed in British Aerospace Service Bulletin SB 27-155, dated August 16, 1991, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced controllability of the airplane, accomplish the following: (a) Within 3 months after the effective date of this AD, inspect the rudder pedal torque tubes (four per airplane) for defects or cracks, using BAe High Frequency Eddy Current Inspection Technique No. 27-20-101, in accordance with British Aerospace Service Bulletin SB 27-155, dated August 16, 1991. (b) If any defects or cracks are detected that exceed the limit specified in British Aerospace Service Bulletin SB 27-155, dated August 16, 1991, prior to further flight, replace them with serviceable components in accordance with the service bulletin. (c) An 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113. (d) 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. (e) The inspections and repairs shall be done in accordance with British Aerospace Service Bulletin SB 27-155, dated August 16, 1991. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. 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. (f) This amendment becomes effective on June 29, 1992.
2013-18-09: We are adopting a new airworthiness directive (AD) for certain Honeywell ASCa Inc. emergency locator transmitters (ELTs) installed on various transport category airplanes. This AD requires various one-time general visual inspections of the ELT transmitter units (TUs), and corrective actions if necessary. This AD was prompted by a fire on a parked and unoccupied airplane; preliminary information indicated combustion in the area of the ELT TU. We are issuing this AD to detect and correct discrepancies of the battery wiring installation inside the TU, which could result in an electrical short and possible ignition source.