Results
2017-14-14: We are adopting a new airworthiness directive (AD) for all Airbus Model A321 series airplanes. This AD was prompted by a determination from fatigue testing that cracks could develop in the cabin floor beam junction at certain fuselage frame locations. This AD requires repetitive inspections for cracking in the cabin floor beam junction at certain fuselage frame locations, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2010-26-10: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model 747-200C, -200F, -400, -400D, and -400F series airplanes. That AD currently requires repetitive inspections for cracks in the overlapping (upper) skin of the upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46; and related investigative and corrective actions, if necessary. This new AD expands the inspection area in the existing AD, and adds a modification of certain lap joints and certain post-repair inspections of the lap joints. Accomplishing the modification would end the repetitive inspections required by the existing AD for the length of lap joint that is modified. This AD results from a structural review of affected skin lap joints for widespread fatigue damage. We are issuing this AD to prevent fatigue cracking in certain lap joints, which could result in rapid depressurization of the airplane.
2001-24-21: This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes, that currently requires a one-time detailed visual inspection to determine if wire segments of the wire bundle routed through the feed through on the aft side of the flight engineer's station are damaged or chafed, and corrective actions, if necessary. This amendment also requires revising the wire bundle support clamp installation at the flight engineer's station. This action is necessary to prevent chafing of the wire bundle located behind the flight engineer's panel caused by the wire bundle coming in contact with the lower edge of the feed through and consequent electrical arcing, which could result in smoke and fire in the cockpit. This action is intended to address the identified unsafe condition.
85-07-07: 85-07-07 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5020. Applies to Model SE3130, SE313B, SA3180, SA318B, SA318C, and SA315B helicopters, certificated in all categories, that are equipped with a tail rotor pitch change control rod that has been modified in accordance with AMS2178. Compliance is required within 50 hours time in service after the effective date of the AD or before the accumulation of 750 hours total time in service for tail rotor gearboxes, whichever occurs later, unless already accomplished. To ensure that proper shot peening of the control rod has been accomplished and thereby prevent possible cracks in the control rod, accomplish the following: (a) Comply with paragraph C of Aerospatiale Service Bulletin No. 01.19 or No. 01.50, dated May 2, 1984, for the appropriate helicopter model. Paragraph C of each bulletin contains disassembly, inspection, and assembly information. (b) Equivalent means of complying with this AD must be approved by the Manager, Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (c) Aircraft may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where compliance may be accomplished. (d) The Director of the Federal Register approved the incorporation by reference of the manufacturer's specifications and procedures identified and described in this directive pursuant to 5 U.S.C. 552(a)(1). Persons may obtain copies of the service bulletins upon request to Aerospatiale Helicopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75051, Attention: Customer Support. The documents may be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas. This amendment becomes effective April 19, 1985.
2017-14-07: We are adopting a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5, V2525-D5, V2528-D5, and V2531-E5 turbofan engines. This AD was prompted following a self- disclosure by IAE regarding manufacturing quality escapes. This AD requires replacing the affected and suspect parts within the time limits specified in the compliance section. We are issuing this AD to address the unsafe condition on these products.
76-21-06: 76-21-06 CESSNA: Amendment 39-2750. Applies to Models 172M (Serial Numbers 17266981 thru 17267584); 172N (Serial Numbers 17267585 thru 67610, 612 thru 621, 623 thru 626, 628 thru 634, 636, 638 thru 648, 651 thru 655, 657, 658, 660 thru 666, 669, 670, 673 thru 679, 681, 682, 684 thru 687, 689, 691 thru 698, 700, 701, 703 thru 706, 708 thru 713, 715, 718, 722 thru 724, 727 thru 729, 732, 736, 738, 739, 74l thru 744, 746 thru 749, 752, 754, 756, 757, 759, 760, 763, 764, 770, 772, 776, 785, 791 and 800); 177B (Serial Numbers 17702450 thru 17702536, 17702538 thru 17702544); and 177RG (Serial Numbers 177RG0875 thru 177RG0990, 177RG0992 thru 177RG0995, 0997 thru 1000, 1002 and 1004) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent loss of engine oil, accomplish the following: A) Before next flight of the affected airplanes, remove the lower engine cowl and visually inspect the engine oil cooler fluid fitting side to determine whetherit is a Model 8406J (S/N 101 thru 1500) or Model 10599A (S/N 101 thru 700). 1. If the oil cooler is not of the model and serial number listed above, make an entry in the aircraft maintenance records indicating that this AD has been accomplished and the airplane may be returned to service. 2. If the oil cooler is of a model and serial number listed above, prior to further flight, replace this cooler with a serviceable oil cooler not of the above model and serial numbers. B. The inspection and maintenance record entry required by Paragraph A(l) may be accomplished by holder of a pilot's certificate issued under Part 61 of the Federal Aviation Regulations on any aircraft owned or operated by him. C. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Cessna Service Letter SE76-17 pertains to this subject. NOTE: A ferry permit to accomplish a needed oil cooler replacementmay be issued under the provisions of FAR 21.197 by FAA District Offices, with appropriate limitations, in coordination with the Chief, Engineering and Manufacturing Branch, FAA. Central Region. This amendment becomes effective October 26, 1976, to all persons except those to whom it was made effective earlier by air mail letters issued September 21, 1976, and October 1, 1976, respectively.
49-34-02: 49-34-02 BELL: Applies to All Model 47D1 Helicopters. Compliance required as soon as possible but not later than September 2, 1949, and daily thereafter. As a result of several fatigue failures of the attaching clamps on the ventral fin and at the attaching bolt holes of the fixed tab, these parts should be visually inspected daily until a permanent fix is available. If cracks are detected, either in the AN 735 clamps, the ventral fin, or the fixed tab, the effected part should be replaced prior to the next flight. (Bell Service Bulletin No. 70 covers the same subject.)
89-22-11: 89-22-11 AIRBUS INDUSTRIE: Amendment 39-6364. Docket No. 89-NM-115-AD. Applicability: Model A300 B4-103 and B4-203 series airplanes, equipped with main landing gear (MLG) barrel hinge arms, Messier Part Number C65381-4 or -6, certificated in any category. Compliance: Required within 12 months after the effective date of this AD, unless previously accomplished. To prevent collapse of one main landing gear, accomplish the following: A. Except as provided in paragraph B., below, replace all main landing gear (MLG) hinge arms having a pad cadmium coating, with either hinge arms that do not have a pad cadmium coating or hinge arms that have been reconditioned in accordance with MHB Service Bulletin 470- 32-652, dated December 30, 1988. Replacement is required in accordance with the procedures specified in Airbus Industrie Service Bulletin A300-32-390, Revision 1, dated December 20, 1988. NOTE: Airbus Service Bulletin A300-32-390 references Messier-Hispano-Bugatti (MHB) Service Bulletin 470-32-651 for additional replacement procedures. B. The following airplanes are not subject to the requirements of this AD: 1. Airplanes equipped with MLG hinge arms to which a pad cadmium coating has been applied in accordance with Airbus Industrie Service Bulletin A300-26-356, dated May 15, 1985 (which references MHB Service Bulletin 470-32-422), and have since undergone a main workshop overhaul and have been subjected to an electrolytic cadmium stripping and replating in a bath. 2. Airplanes equipped with MLG hinge arms that have been reconditioned in accordance with MHB Service Bulletin 470-32-652. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either 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 airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6364, AD 89-22-11) becomes effective on November 20, 1989.
2001-24-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -30, and -40 series airplanes and C-9 airplanes, that requires an inspection to detect chafing of the wiring of the attendants' work light of the aft cabin, and repair of chafed wiring. This AD also requires modification and reidentification of the attendants' work light assemblies of the aft cabin. This action is necessary to prevent chafing of the ground wire against the positive contact of the lamp of the attendants' work light of the aft cabin, and consequent arcing or arcing damage to the wiring of the attendants' work light and transformer of the aft cabin. Such arcing or arcing damage could result in short circuits and consequent smoke and fire in the aft cabin area. This action is intended to address the identified unsafe condition.
86-01-06: 86-01-06 AIRBORNE DIVISION, PARKER HANNIFIN CORPORATION: Amendment 39-5206. Applies to the following Airborne Dry Air Pumps and Auxiliary Dry Air Pumps installed on piston engine airplanes certificated in any category: AIRBORNE PART NUMBER SERIAL NUMBERS Dry Air Pumps 241CC-13 10AA30 thru 10AA36 and 10AA38 242CW 10AA281 thru 10AA293 441CC 9AA260 thru 9AA288 9AA291, 9AA294, 9AA295 441CC-7 9AA929 thru 9AA-949 9AA953, 9AA954, 9AA956, 9AA957, 9AA959 442CW 9AA850 thru 9AA875, 9AA880 thru 9AA886, 9AA888 thru 9AA903, 9AA905 thru 9AA921, 9AA928, 9AA934, 9AA936, 9AA939, 9AA940, 9AA945 thru 9AA952, 9AA955 thru 9AA958, 9AA962 thru 9AA967 442CW-4 10AA173 thru 10AA179 10AA182 thru 10AA199 10AA201, 10AA202 442CW-12 10AA356, 10AA357, 10AA386, 10AA389 Auxiliary Dry Air Pumps 4A2-1 9AA44 thru 9AA46 4A3-1 9AA56, 9AA59 thru 9AA66, 9AA73, 9AA79 thru 9AA82, 10AA83 thru 10AA88, 10AA90 thru 10AA94, 10AA96, 10AA114, 10AA126, 10AA130, 10AA131, 10AA132, 10AA138, 10AA150, 10AA154, 10AA155, 10AA159, 10AA161 NOTE: These pumps were not available for installation before September 1, 1985. Therefore, new Airborne Dry Air Pumps or Auxiliary Dry Air Pumps installed previous to that date are exempt from this AD. Pumps that have been reworked by Airborne will have a white date code stamped on the pump housing near the discharge port. This will indicate that the pump complies with this AD. COMPLIANCE: Required as indicated, unless previously accomplished. To prevent premature failure of the Airborne Dry Air and Auxiliary Dry Air Pumps, accomplish the following: (a) For Dry Air Pumps P/N's 241CC-13, 242CW, 441CC, 441CC-7, 442CW, 442CW-4, and 442CW-12, prior to further flight in IFR conditions, inspect installed dry air pump(s) to determine if one of the subject pumps is installed. (1) If one of these pumps is installed, and if the airplane is equipped for IFR flight, fabricate using minimum 0.10 inch letters, and install a placard in full view of the pilot which states; "FLIGHT IN IFR CONDITIONS PROHIBITED", and operate in accordance with this limitation. (2) And within 15 days of the effective date of this AD, replace the subject pump and remove the placard. Return pump to Airborne as described in Airborne Service Letter No. 30, dated November 11, 1985. (b) For Airborne Auxiliary Dry Air Pump P/N 4A2-1 or 4A3-1, prior to further flight in IFR conditions, inspect the auxiliary dry air pump if installed, to determine if one of the subject pumps is installed. (1) If one of these pumps is installed, fabricate using a minimum of 0.10 inch letters and install a placard in full view of the pilot which states; "STANDBY VACUUM SYSTEM MAY BE INOPERATIVE DUE TO VACUUM PUMP MALFUNCTION". (2) And within 30 days of the effective date of this AD, replace the subject pump and remove the placard. Return pump to Airborne as described in Airborne Service Letter No. 30, dated November 11, 1985. (c) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (d) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 232, Des Plaines, Illinois 60018, Telephone (312) 694-7357. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Betty Annable, Parker Hannifin Corp., Airborne Division, 711 Taylor Street, Elyria, Ohio 44036 or the FAA, Rules Docket, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 31, 1986.