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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 NOTE 1: Compliance with superseded AD 92-16-11 is considered "unless already accomplished" for the initial inspection and modification requirements of this AD except as specified in paragraph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.