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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.
2013-18-01: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B, EC155B1, SA-365N, SA- 365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters. This AD requires inspecting the collective pitch lever for correct locking and unlocking conditions. This AD was prompted by two separate reports of inadvertent collective pitch lever locking and unlocking. The actions of this AD are intended to detect an incorrectly adjusted collective pitch lever, which could result in loss of control of the helicopter.
2000-12-15: This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Falcon 2000, Mystere-Falcon 900, Falcon 900EX, Fan Jet Falcon, Mystere-Falcon 50, Mystere-Falcon 20, Mystere-Falcon 200, and Falcon 10 series airplanes, that requires repetitive tests and inspections to detect discrepancies of the overwing emergency exit; and corrective action, if necessary. 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 overwing emergency exits to open, and consequent injury to passengers or crew members during an emergency evacuation.
2013-18-04: We are adopting a new airworthiness directive (AD) for all PIAGGIO AERO INDUSTRIES S.p.A Model P-180 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 cracks at the joint between the hinge pin sub-assembly and the lock pin of the main landing gear lever hinge fitting. We are issuing this AD to require actions to address the unsafe condition on these products.
2021-18-06: The FAA is superseding Airworthiness Directive (AD) 2021-11- 03, which applied to certain Airbus Helicopters Model EC 155B, EC155B1, SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. AD 2021-11-03 required inspecting the main gearbox (MGB) fixed cowling front fitting (MGB front fitting), and depending on findings, corrective action. This AD retains the requirements of AD 2021-11-03, and includes service information that was omitted for Airbus Helicopter Model EC 155B and EC155B1 helicopters, as specified in a European Aviation Safety Agency (now 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.
2003-11-21: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332 C, L, and L1 helicopters. This action requires revising the Rotorcraft Flight Manual (RFM) Limitations section if certain fuel control units are installed. This AD is prompted by the discovery of an anomaly in certain fuel control units that may lead to inadequate fuel flow in single-engine flight. This condition, if not corrected, could result in failure of the engine to develop the maximum 2 1/2 minute one engine inoperative (OEI) power, reduced helicopter performance, and subsequent loss of control of the helicopter during OEI operation.
75-02-05: 75-02-05 MCDONNELL DOUGLAS: Amendment 39-2070. Applies to Models DC-8-20, -30, -40, -50, and -60 Series airplanes, certificated in all categories. \n\n\tCompliance required as indicated. \n\n\tTo reduce potential fire hazard existing in lavatory waste containers of McDonnell Douglas Models DC-8-20, -30, -40, -50, and -60 Series airplanes, accomplish the following: \n\n\t(a)\tWithin 300 hours time in service from the effective date of this airworthiness directive, unless already accomplished within the last 1,000 hours, perform a thorough inspection of all electrical appurtenances, including wiring, terminal boxes, switches, and hot water heaters, physically located within lavatory waste container areas for wear, abrasion and corrosion. Repair or replace as necessary. \n\n\t(b)\tBy December 31, 1975, unless already accomplished, modify the existing lavatory waste containers in accordance with McDonnell Douglas All Operators Letter (AOL) 8-676A, dated December 16, 1974, and enclosed data,as applicable, or later FAA-approved revisions, or in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(c)\tAircraft may be operated to a base for accomplishment of maintenance required under this airworthiness directive, per FAR's 21.197 and 21.199. \n\n\tThis amendment becomes effective January 24, 1975.
75-20-02: 75-20-02 BOEING: Amendment 39-2369 as amended by Amendment 39-2501. Applies to Model 737 series airplanes, Line Nos. 1 through 299 inclusive, certificated in all categories. Compliance required as indicated unless already accomplished. \n\tTo prevent unwanted trailing edge flaps retraction and leading edge flap extension, accomplish the following: \n\tA.\tAirplane Line Nos. 1 through 269 with flap power unit assemblies not modified in accordance with Boeing Service Bulletin 737-27-1041, Revision 4, Part II, or later FAA approved revisions, within the next 750 landings, unless accomplished within the last 250 landings, and at times thereafter not to exceed 1,000 landings, inspect the flap power unit in accordance with paragraph C. \n\tB.\tAirplane Line Nos. 270 through 299, or those earlier aircraft with flap power unit assemblies modified per Boeing Service Bulletin 737-27-1041, Revision 4, Part II, or later FAA approved revisions, within the next 750 landings, unless inspected within the last 750 landings, inspect in accordance with paragraph D.\n \tC.\tInspect the worm teeth in the flap power unit for wear in accordance with Boeing Service Bulletin 737-27-1041, Revision 4, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Flap power unit assemblies with worm teeth worn beyond the limits prescribed in the service bulletin, must be modified prior to further flight in accordance with Boeing Service Bulletin 737-27-1041, Revision 4, Part II, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Repetitive inspections for modified units are to be made in accordance with paragraph E. \n\tD.\t1. Inspect the worm gear for wear in accordance with either inspection procedure in Boeing Service Bulletin 737-27-1076, Revision I, Part III, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Repetitive inspections are to be accomplished at intervals specified in either Method I or Method II of paragraph B, Part III, of the service bulletin, but not to exceed 5,000 landings for Method I or 3,000 landings for Method II. \n\t\t2.\tFlap power unit assemblies with worm gears worn beyond the limits specified in the service bulletin are to be replaced with new parts prior to further flight. \n\tE.\tFlap power units repaired in accordance with paragraph C or D2 must be inspected during 1400-1600 landings after new parts are installed, in accordance with paragraph D1 above, and thereafter comply with paragraph D. \n\tF.\tThe inspections required by this directive may be terminated when the mechanical trailing edge flap asymmetry system has been replaced with the electrical system in accordance with Boeing Service Bulletin No. 737-27-1079 and; \n\t\t1.\tA new worm gear has been installed in the trailing edge flap drive power unit in accordance withBoeing Service Bulletin No. 737-27-1076, or the existing worm gear has been inspected in accordance with Service Bulletin No. 737-27-1076 and no perceptible wear groove can be identified on the side of any tooth, or other modifications approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region are made and, \n\t\t2.\ta new worm has been installed in the trailing edge flap power drive unit in accordance with Boeing Service Bulletin No. 737-27-1041 Revision 4, or the existing worm has been inspected in accordance with Service Bulletin No. 737-27-1041 Revision 4 and no perceptible wear groove can be identified in the side of any tooth, or other modifications approved by Chief, Engineering and Manufacturing Branch, FAA Northwest Region are made. \n\tG.\tUpon request by an operator, through an appropriate FAA maintenance inspector, subject to approval by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, the repetitive inspection period herein may be adjusted for that operator if the request contains adequate substantiating data to justify the increase. \n\tH.\tFor the purposes of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings on the flap power unit worm gear may be determined by actual count or by dividing each airplane's hours time in service since the flap power drive unit was installed, by the operator's fleet average time from takeoff to landing for the airplane type. \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)(1).\n \tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington.Amendment 39-2369 became effective October 27, 1975. \n\tThis Amendment 39-2501 becomes effective February 9, 1976.
2003-11-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-100 and 727-200 series airplanes, that requires, under certain conditions, replacement of the installed autopilot pitch control computer with a modified computer, testing of the modified system, and revision of the Airplane Flight Manual (AFM). The actions specified by this AD are intended to prevent undesirable and potentially dangerous pitch oscillations during coupled instrument landing system (ILS) approaches. This AD is intended to address the identified unsafe condition.
2018-07-03: We are superseding Airworthiness Directive (AD) 2018-02-05 for certain Piper Aircraft, Inc. Models PA-28-140, PA-28-150, PA-28-151, PA-28-160, PA-28-161, PA-28-180, PA-28-181, PA-28-236, PA-28-201T, PA- 28R-180, PA-28R-200, PA-28R-201, PA-28R-201T, PA-28RT-201, and PA-28RT- 201T airplanes. AD 2018-02- [[Page 14569]] 05 required inspecting the fuel tank selector cover to verify the left and right fuel tank selector placards are located at the proper positions and replacing those that are improperly located with new placards. This AD addresses the same unsafe condition and requires the same actions as AD 2018-02-05, but changes the inspection of the fuel tank selector cover to a preflight check and allows for various fuel selector clocking configurations. This AD was prompted by our determination to allow the owner/operator (pilot) holding at least a private pilot certificate to perform the preflight check. We are issuing this AD to allow the pilot to do a preflight check of the fuel selector placards.
2013-18-06: We are adopting a new airworthiness directive (AD) for Bell Model 206A, 206B, 206L, 206L-1, 206L-3, 206L-4, 222, 222B, 222U, 230, 407, 427, and 430 helicopters. This AD requires inspecting each bearing to determine if it has been properly staked and replacing the bearing or assembly if it has not been properly staked. This AD was prompted by bearings not being properly staked and migrating out of their proper position, which may limit the functionality of the affected part. The actions of this AD are intended to prevent failure of a bearing and the assembly in which it is installed and subsequent loss of control of the helicopter.