Results
98-12-26: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time inspection to determine the torque values of the coupling fitting attachment bolts at fuselage station 10790, 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 loss of the coupling fitting attachment bolts between the center wing section and the fuselage, and consequent reduced structural integrity of the airplane.
83-22-08: 83-22-08 B.F. GOODRICH: Amendment 39-4765. Applies to B.F. Goodrich Emergency Evacuation Slide/Rafts P/Ns 7A1340 series, 7A1342 series, 7A1371 series, and 7A1373 series. These slide/rafts are installed on Boeing Model 747-100 and 747-200B airplanes in accordance with Supplemental Type Certificate (STC) SA574GL, and on Boeing Model 747-100B, 747SR, and 747-300 airplanes in accordance with STC SA575GL. Compliance required as indicated below. To assure proper functioning of B.F. Goodrich Slide/Rafts, accomplish the following unless previously accomplished in accordance with the procedures in B.F. Goodrich Service Bulletin 25-081, Revision 1, dated September 27, 1983. \n\n\tA.\tFor B.F. Goodrich Slide/Rafts, P/Ns 7A1340 series or 7A1371 series S/Ns G001 thru G289, and P/Ns 7A1342 series or 7A1373 series, S/Ns G001 thru G087: Within 20 calendar days after the effective date of this AD perform the maintenance procedures contained in B. F. Goodrich Service Bulletin 25-081, Revision 1, dated September 27, 1983, or subsequent FAA approved revisions, on installed slide/rafts or on slide/rafts prior to installation. Repeat inspections per paragraph C., below. \n\n\tB.\tFor all B.F. Goodrich Slide/Rafts, P/N's 7A1340 series, 7A1342 series, 7A1371 series and 7A1373 series, inspect all serial numbers installed prior to September 1, 1983, and not inspected per paragraph A., above, in accordance with B.F. Goodrich Service Bulletin 25-081, Rev. 1, dated September 27, 1983, or subsequent FAA approved revision, within 120 days of the effective date of this AD. Slides installed subsequent to August 31, 1983, must be inspected in accordance with B.F. Goodrich Service Bulletin 25-081, Revision 1, dated September 27, 1983, or subsequent FAA approved revision, within 180 days of last leak check inspection. (Reference Service Bulletin Section 2B.) Repeat inspections per Paragraph C., below. \n\n\tC.\tTo prevent undetected deterioration repeat the inspection of all installed B.F. Goodrich Slide/Rafts, P/Ns 7A1340 series, 7A1342 series, 7A1371 series and 7A1373 series, in accordance with Section 2B of B.F. Goodrich Service Bulletin 25-081, Rev. 1, dated September 27, 1983, or subsequent FAA approved revision, within 180 days of last inspection or within 180 days of installation. \n\n\tD.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Chicago Aircraft Certification Office, FAA, Central Region. \n\n\tE.\tUpon request of operator, an FAA Principal Maintenance Inspector, subject to prior approval by Manager, Chicago Aircraft Certification Office, FAA, Central Region, can adjust the compliance times if the request contains substantiating data to justify the increase for the operator. \n\n\tF.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to B.F. Goodrich Company, Attn: Mr. Earl Lucas, Dept. 1809, Bldg. 17F, 500 South Main Street, Akron, Ohio 44318. \n\n\tThese documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington. \n\n\tThis amendment becomes effective November 15, 1983.
86-01-51 R1: 86-01-51 R1 BOEING: Amendment 39-5269. Applies to all Model 747 series airplanes equipped with General Electric CF6 engines, certificated in any category. To prevent accumulation of flammable fluid in the engine strut, which constitutes a fire hazard, accomplish the following, unless already accomplished: \n\n\t1.\tWithin the next 72 hours time-in-service, inspect and, if necessary, clear the engine strut drains in accordance with the procedures specified in Chapter 71-71-00 of Boeing Maintenance Manual for the Boeing Model 747 airplanes equipped with General Electric CF6 engines. Repeat these inspections at intervals not to exceed 1,000 hours time-in-service. Report results of inspections to FAA, Northwest Mountain Region, Seattle Aircraft Certification Office, Propulsion Branch, ATTN: Kanji Patel, ANM-140S, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168. \n\n\t2.\tThe repetitive inspections required by paragraph 1., above, may be terminated upon the accomplishment of the following: \n\n\t\tA.\tFor Group I and II airplanes defined in Boeing Service Bulletin 747-71-2146, dated November 24, 1978, accomplish the replacement of the inboard and outboard pylon drain lines only, as shown in Figures 2 and 3, respectively, of that service bulletin or later FAA-approved revisions. \n\n\t\tNOTE: The portion of this service bulletin pertaining to "Strut Pylon Drain Line Engine Tube Replacement," Figure 1, has been superseded by Boeing Service Bulletin 747-71-2155, Revision 3, dated September 28, 1984. \n\n\t\tB.\tFor Group I airplanes, as defined in Boeing Service Bulletin 747-71-2155, Revision 3, dated September 28, 1984, accomplish replacement of the engine strut aft drain and incorporate the bracket/heat shield, in accordance with Work Package I described in that service bulletin, or later FAA-approved revisions; and install forward drain fitting, drain tube, and fluid dam in accordance with Work Package II described in that same service bulletin, or later FAA-approved revisions. \n\n\t\tC.\tFor Group II airplanes, as defined in Boeing Service Bulletin 747-75-2155, Revision 3, dated September 28, 1984, install forward drain fitting, drain tube, and fluid dam in accordance with Work Package II described in that service bulletin, or later FAA-approved revisions. \n\n\t\tD.\tFor Group III airplanes, as defined in Boeing Service Bulletin 747-75-2155, Revision 3, dated September 28, 1984, accomplish replacement of the engine strut aft drain and incorporate the bracket/heat shield, in accordance with Work Package I described in that service bulletin, or later FAA-approved revisions. \n\n\t\tE.\tFor Group I, II, and IV airplanes, as defined in Boeing Service Bulletin 747-75- 2155, Revision 3, dated September 28, 1984, accomplish Work Package III, in accordance with that service bulletin, or later FAA-approved revisions, if the thrust reverser follow-up cable support bracket is found to interfere with the fluid dam. \n\n\t3.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA Northwest Mountain Region. \n\n\t4.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspections and, if necessary, cleaning of the engine strut drain lines. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective April 18, 1986, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T86-01-51, issued on January 9, 1986.
2012-21-15: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by events of excessive rudder pedal inputs and consequent high loads on the vertical stabilizer on several airplanes. This AD requires either incorporating a design change to the rudder control system and/ or other systems, or installing a stop rudder inputs warning (SRIW) modification. We are issuing this AD to prevent loads on the vertical stabilizer that exceed ultimate design loads, which could cause failure of the vertical stabilizer and consequent reduced controllability of the airplane.
98-12-15: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS 332C, L, L1, and L2 helicopters that requires visually inspecting the intermediate gearbox-to-structure attachment stirrup (stirrup) front tabs for cracks, and if a crack is discovered, removing the intermediate gearbox and replacing it with an airworthy intermediate gearbox; and inspecting for the conformity of the attachment parts. This amendment is prompted by five reports of failure of the two stirrup tabs. The actions specified by this AD are intended to prevent failure of the intermediate gearbox stirrup front tabs, loss of anti-torque drive, and subsequent loss of control of the helicopter.
98-12-16: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA 330F, G, and J helicopters that requires visually inspecting the intermediate gearbox (IGB) fairing safety stop (safety stop) for cracks, crazing, or edge wear, and if a crack, crazing, or edge wear exceeds the established limits, replacing the safety stop; and, inspecting to ensure that the inclined drive shaft fairing hinge pin is properly locked. A terminating action is provided in the AD by installing an additional safety stop on the IGB fairing. This amendment is prompted by one report of an accident involving the loss of the inclined drive shaft fairing. The actions specified by this AD are intended to prevent loss of the inclined drive shaft fairing, impact with the tail rotor, and subsequent loss of control of the helicopter.
98-12-10: This amendment supersedes Airworthiness Directive (AD) 93-10-11, which currently requires installing an inspection opening in the wing, repetitively inspecting the upper wing spar cap for cracks, and repairing any cracks on all Avions Mudry et Cie (Avions) Model CAP 10B airplanes. This AD will retain the same actions already required by AD 93-10-11, and will add inspecting, and repairing if necessary, the lower surface of the wing spar. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent structural cracks in the wing spar, which could lead to loss of a wing and loss of control of the airplane.
79-09-03: 79-09-03 BOEING: Amendment 39-3454. Applies to all Model 747 series airplanes certificated in all categories. Compliance required within 500 hours time-in-service after the effective date of this AD unless already accomplished. \n\tTo prevent takeoff with a takeoff aural warning system that would not indicate an unsafe takeoff condition, accomplish the following: \n\tPerform a one-time check of the aural warning system and, as necessary, adjust and re- check the aural warning activation switch, the auto-brake deactivation and auto-speedbrake retraction switches in accordance with Boeing Alert Service Bulletin 747-31A2056, Rev. 1, dated April 6, 1979, or later FAA approved revisions, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Northwest Region. \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. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective May 10, 1979.
81-19-05: 81-19-05 McDONNELL DOUGLAS: Amendment 39-4216. Applies to McDonnell Douglas Model DC-9-80 series airplanes, certificated in all categories with thrust reverser barrel assemblies P/N 5938033-1 installed. Compliance required as indicated unless already accomplished. To prevent the separation of the thrust reverser from the airplane as a result of a failure of the brazed joint at the thrust reverser attach flange, accomplish the following:\n\n\tA.\tWithin three days from the effective date of this AD, and at intervals of 24 hours calendar time thereafter, conduct a visual inspection, with a 3 to 5 power magnifying glass, of the exhaust nozzle barrel assembly exterior skin P/N 5938033-5 at attach flange P/N 5938033-37 joint for buckling, obvious separation, or circumferential cracks especially in the zone 30 degrees above and below the thrust reverser stang fairings on each side. If buckling separation or cracks are found remove and replace barrel assembly prior to further flight. Chapter 78-30-01 of the maintenance manual contains additional information on this subject.\n\n\tB.\tWithin three days from the effective date of this AD inspect all thrust reversers to identify each thrust reverser barrel serial number. Remove from service reverser assemblies identified by the following barrel serial numbers.\n\n\tAccomplishment instructions for this inspection are contained in McDonnell Douglas Alert Service Bulletin A78-50 Revision 1, dated July 20, 1981, or later revisions approved by the Chief, Los Angeles Area Aircraft Certification Office, Northwest Region.\n\n\tSerial Numbers D3-0005, D3-0008, D3-0010 thru D3-0012, D3-0024, D3-0025, D3-0043, D3-0047, D3-0048, D3-0057, D3-0058, D3-0060, D3-0063, D3-0064, D3-0069, D3-0084, D3-0091, D3-0093, D3-0095, D3-0100 thru D3-0105, D3-0108, D3-0112, D3-0113, D3-0115, D3-0119, D3-0129A, D3-0132, D3-0137, D3-0156, D3-0162, D3-0165, and D3-0172. \n\n\tNOTE:\n\n\tTypical example of the number found on the reverser barrel assembly is "5938033-1-01-D3-0105." This number is located approximately six inches aft of the upper hydraulic thrust reverser latch and is etched on the exterior surface of the thrust reverser exhaust duct barrel assembly near top centerline. 5938033-1 is the part number and will be the same on each unit. The last six digits (D3-0105) constitute the listed serial number.\n\n\tC.\tWithin 120 days from the effective date of the AD modify all P/N 5938033-1 reverser barrel assemblies by welding the engine attach flange - outer barrel skin joint in accordance with the accomplishment instructions of McDonnell Douglas Service Bulletin 78-51 dated August 25, 1981, or later revisions approved by the Chief, Los Angeles Area Aircraft Certification Office, Northwest Region. Upon completion of this modification reidentify the reverser barrel assembly as P/N 5938033-501 and the thrust reverser assembly as P/N 5938050-501 in accordance with paragraph 2.B. (6) and (9) of the accomplishment instructions of the bulletin. This modification constitutes terminating action for all requirements of this AD. All reverser barrel assemblies removed from service per paragraph B above may be modified in accordance with this paragraph and returned to service.\n\n\tD.\tSpecial flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.\n\n\tE.\tAlternative means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Region. \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\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108, or 4344 Donald Douglas Drive, Long Beach, California 90808.\n\n\tThis amendment becomes effective September 28, 1981.
98-12-14: This amendment adopts a new airworthiness directive (AD) that applies to certain AERMACCHI S.p.A. (AERMACCHI) S.205 series and Models S.208 and S.208A airplanes. This AD requires inspecting the flap cable pulley bracket for correct alignment and correcting any misalignment; inspecting the flap control cable for wear (nicks, cuts, frays, etc.), and replacing the flap control pulley bracket and flap control cable if worn. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent flap control failure, which could result in loss of control of the airplane.