Results
2006-07-23: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 757 airplanes. This AD requires repetitive measurements of the freeplay of each of the three power control units (PCUs) that move the rudder; repetitive lubrication of rudder components; and corrective actions if necessary. This AD results from a report of freeplay-induced vibration of the rudder. The potential for vibration of the control surface should be avoided because the point of transition from vibration to divergent flutter is unknown. We are issuing this AD to prevent excessive vibration of the airframe during flight, which could result in divergent flutter and loss of control of the airplane.
86-01-05: 86-01-05 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5210. Applies to Lockheed Model L-1011-385 series airplanes, certificated in any category, equipped with Dynamic Controls Corporation oxygen initiator sequence timer switch(es), Part Numbers 11035-2/-3. Compliance is required as indicated, unless previously accomplished. To prevent malfunction of the passenger oxygen system when activated, due to dormant shorted transient suppression capacitors in the oxygen initiator sequence timer switch(es), accomplish the following: A. Within 30 days after the effective date of this AD, perform a resistance check of oxygen initiator sequence timer switch(es) in accordance with Lockheed Service Bulletin 093- 35/041, Part I, dated December 18, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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 information from the manufacturer may obtain copies upon request to Lockheed-California Company, P. O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This amendment becomes effective January 21, 1986.
2018-26-01: We are superseding Airworthiness Directive (AD) 2018-18-01 for all CFM International S.A. (CFM) Model CFM56-7B turbofan engines. AD 2018-18-01 required initial and repetitive inspections of certain fan blades and, if they fail the inspection, their replacement with parts eligible for installation. This AD requires the same initial and repetitive inspections but revises the compliance time for the initial inspections and revises the installation prohibition based on the updated compliance time. This AD was prompted by further analysis by the manufacturer that indicated a need to reduce the initial fan blade inspection interval based on an ongoing root cause investigation of an April 2018 engine failure. We are issuing this AD to address the unsafe condition on these products.
87-05-07: 87-05-07 CASA: Amendment 39-5560. Applies to the CASA Model C-212 series airplanes, serial numbers as listed in CASA Service Bulletin 212-25-32, dated October 23, 1985, certificated in any category. Compliance is required within 8 months after the effective date of this AD. To prevent obstruction of an evacuation path to an emergency exit, accomplish the following, unless previously accomplished: A. Modify the attendant's seat in accordance with CASA Service Bulletin 212-25-32, dated October 23, 1985. B. 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. C. Special 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 modification required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Construcciones Aeronauticas S.A., Getafe, Madrid, Spain. This document 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. This amendment becomes effective March 25, 1987.
99-26-19: This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) J-2 series airplanes equipped with wing lift struts. This AD requires repetitively inspecting the wing lift struts for dents and corrosion and the wing lift strut forks for cracks; replacing any strut found with corrosion or dents, or forks with cracks; and repetitively replacing the wing lift strut forks. This AD also requires incorporating a "NO STEP" placard on the lift strut. This AD is the result of the Federal Aviation Administration (FAA) inadvertently omitting the J-2 series airplanes from the applicability of AD 99-01-05. The actions specified by this AD are intended to prevent in-flight separation of the wing from the airplane caused by wing lift struts with dents or corrosion or wing lift forks with cracks, which could result in loss of control of the airplane.
86-08-07: 86-08-07 TELEDYNE CONTINENTAL MOTORS: Letter issued April 21, 1986. Applies to TSIO-520- BE reciprocating engines with the following serial numbers installed on Piper PA-46 (Malibu) airplanes: ENGINE SERIAL NUMBERS 528026 528222 528233 528246 528085 528223 528234 528252 528205 528224 528235 528253 528208 528225 528236 528254 528215 528226 528237 528255 528216 528227 528238 528256 528217 528228 528239 528259 528219 528229 528240 528260 528220 528230 528242 528263 528221 528231 528243 Prior to further flight, remove the engine driven fuel pump assembly (P/N 646571-1) and replace with fuel pump assembly (P/N 649374-1). Upon request, an equivalent means of compliance with the requirements of this priority letter AD may be approved by the Manager, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, Georgia 30337. This airworthiness directive is effective upon receipt.
2006-07-19: The FAA is adopting a new airworthiness directive (AD) for certain Aerospatiale Model ATR42 airplanes and Model ATR72 airplanes. This AD requires installing protective ramps on trim panel 110VU; and inspecting the protective guard of the standby pitch trim switch to determine if it is missing, damaged, or ineffective, and doing the corrective action if necessary. This AD results from a finding that the protective guard of the standby pitch trim switch, which is installed on the center pedestal, could be damaged or missing. We are issuing this AD to prevent inadvertent activation of the standby pitch trim, which could result in pitch trim runaway and consequent reduced controllability of the airplane.
2006-07-20: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Makila 1 A2 turboshaft engines. This AD requires upgrading the software version of the digital electronic control. This AD results from Turbomeca determining that Makila 1 A2 turboshaft engines with software version 9 installed in the digital electronic control unit (DECU), under certain conditions, could experience a free turbine overspeed and uncontained failure. We are issuing this AD to prevent overspeed and uncontained failure of the free turbine and damage to the helicopter.
99-01-05: This amendment supersedes Airworthiness Directive (AD) 93-10-06, which currently requires repetitively inspecting the wing lift struts and wing lift strut forks for cracks or corrosion on all airplane models of The New Piper Aircraft, Inc. (Piper) that are equipped with wing lift struts, and replacing any strut or fork found cracked or corroded. This AD clarifies certain requirements of AD 93-10-06, eliminates the lift strut fork repetitive inspection requirement on the Piper PA-25 series airplanes, incorporates models inadvertently omitted from AD 93-10-06, and requires fabricating and installing a placard on the lift strut. This AD results from reports, questions, and information received from the field on AD 93-10-06, which show a need to clarify and add information that will more fully achieve the safety intent of that AD. The actions specified by this AD are intended to prevent in-flight separation of the wing from the airplane caused by corroded wing lift struts or cracked wing lift forks, which could result in loss of control of the airplane.
85-19-05: 85-19-05 BURKHART GROB: Amendment 39-5133. Applies to model G109 powered gliders certificated in any category. Compliance is required as indicated unless already accomplished. To prevent undesirable spinning, accomplish the following before further flight: (a) Replace the applicable pages of the flight manual with those contained in Grob- Werke GmbH Technical Information TM 817-10/2 dated May 2, 1983, and revise the wording of the spin warning placard on page 18e to read "AEROBATIC MANEUVERS INCLUDING SPINNING PROHIBITED" instead of "AEROBATIC INCLUSIVE SPINNING PROHIBITED". (b) Install spin warning placard on the left hand side of the instrument panel which reads "AEROBATIC MANEUVERS INCLUDING SPINNING PROHIBITED". Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium 09667-1011, telephone 513.38.30. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, may adjust the compliance time specified in this AD. This amendment becomes effective September 25, 1985.
98-20-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flight crew with revised procedures for checking the flap system. This AD also requires revising the maintenance program to provide procedures for checking the flap system, and performing follow-on actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent an unannunciated failure of the flap system, which could result in a flap asymmetry, and consequent reduced controllability of the airplane.
2018-25-17: We are adopting a new airworthiness directive (AD) for Air Comm Corporation (Air Comm) air conditioning systems installed on various model helicopters. This AD requires replacing electrical connectors and prohibits the installation of other parts. This AD was prompted by reports of overheated connectors. The actions of this AD are intended to address an unsafe condition on these products.
2006-07-08: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. This AD requires repetitive inspections for stress corrosion cracks of the main fuselage frame, and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from several reports of cracking of the main fuselage frame. We are issuing this AD to detect and correct stress corrosion cracking of the main fuselage frame, which could result in extensive damage to adjacent structure and reduced structural integrity of the airplane.
2006-07-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-131, -231, and -232 airplanes. This AD requires inspecting for cracks or failure of the primary load path components of the engine forward mount, and corrective action if necessary. This AD also requires removing, re-installing, and re-torquing the attachment bolts for the secondary load path. This AD results from a report that, during modification of certain engine forward mount assemblies of the left and right engines done at an engine shop visit, an incorrect torque was applied to the attachment bolts. We are issuing this AD to prevent structural failure of the secondary load path of the forward engine mount, which, if combined with failure of the primary load path, could result in separation of the engine from the airplane.
2018-25-14: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by reports of electrical arcing between the auxiliary power unit (APU) starter motor positive terminal and the APU fuel drain line. This AD requires the removal of certain clamps and replacement of the flexible APU fuel drain line. We are issuing this AD to address the unsafe condition on these products.
2006-07-04: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires repetitive general visual inspections for dirt, debris, and drain blockage and cleaning of the aft fairing cavities of the engine struts; and modification of the aft fairings, which terminates the repetitive general visual inspections. This AD results from a report indicating that water had accumulated in the cavities of the engine strut aft fairings. We are issuing this AD to prevent drain blockage by debris that, when combined with leaking, flammable fluid lines passing through the engine strut aft fairing, could allow flammable fluids to build up in the cavity of the aft fairing, and consequently could be ignited by the engine exhaust nozzle located below the engine strut, resulting in an explosion or uncontrolled fire.
93-24-14: 93-24-14 PIPER AIRCRAFT CORPORATION: Amendment 39-8762; Docket No. 93-CE- 17-AD. \nApplicability: PA34 Series airplanes (all models and serial numbers), certificated in any category. \n\n\tCompliance: Required within the next 100 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished within the last 400 hours TIS prior to the effective date of this AD, and thereafter at intervals not to exceed 500 hours TIS. \n\n\tTo prevent the nose landing gear from collapsing because of failure of the bolt that connects the upper drag link to the nose gear trunnion, which could lead to airplane damage, accomplish the following: \n\n\t(a)\tReplace the bolt and stack up that connects the upper drag link to the nose gear trunnion with new parts of the following in accordance with Figure 1 of this AD: \n\n\t\t(1)\tPiper part number (P/N) 400 274 (AN7-35) bolt. \n\n\t\t(2)\tPiper P/N 407 591 (AN960-716L) washer, as applicable. \n\n\t\t(3)\tPiper P/N 407 568 (AN960-716) washer, as applicable. \n\n\t\t(4)\tPiper P/N 404 396 (AN320-7) nut; and \n\n\t\t(5)\tPiper P/N 424 085 cotter pin. \n\n\t(b)\tSpecial 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. \n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. \n\n\t(d)\tAll persons affected by this directive may obtain copies of the document referred to herein upon request to the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. \n\n\t(e)\tThis amendment (39-8762) becomes effective on January 28, 1994. \n\n\n\n\t\t\t\t FIGURE 1\n\t\t\t\t \t AD 93-24-14
85-07-08: 85-07-08 BRITISH AEROSPACE: Amendment 39-5032. Applies to Model HS/BH/DH 125 series airplanes with the serial numbers listed in the applicability statement of British Aerospace HS 125 Service Bulletin 23-21-(8765), dated March 22, 1983. Compliance is required within 180 days after the effective date of this AD, unless previously accomplished. To prevent failure of the audio communication system, accomplish the following: A. Modify the power supply system in accordance with the accomplishment instructions of British Aerospace HS 125 Service Bulletin 23-21-8765, dated March 22, 1983. B. Alternate 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. C. Special 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. Thisamendment becomes effective May 13, 1985.
91-20-06: 91-20-06 BOEING: Amendment 39-8040. Docket 91-NM-56-AD. Supersedes AD 89-22-03. \n\n\tApplicability: Model 747-100 and -200 series airplanes, manufactured prior to January 1, 1981; equipped with General Electric CF6-45/50 or Pratt and Whitney JT9D-70 engines; as listed in Boeing Service Bulletin 747-26-2162, dated September 20, 1990, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo preclude cross connection of the engine nacelle fire extinguishing plumbing during maintenance, accomplish the following: \n\n\tA.\tWithin 10 days after October 24, 1989 (the effective date of Amendment 39- 6353, AD 89-22-03), and thereafter, immediately following any maintenance action which could cause mis-plumbing, conduct an inspection of the engine fire extinguishing system plumbing in accordance with Boeing Service Bulletin 747-26A2094, Revision 1, dated March 25, 1983. \n\n\tB.\tBefore further flight, correct any discrepancy detected during the functional tests required by paragraph A. of this AD. \n\n\tC.\tWithin 18 months after the effective date of this amendment, modify the engine fire extinguisher system plumbing in accordance with Boeing Service Bulletin 747-26-2162, dated September 20, 1990. Accomplishment of this modification constitutes terminating action for the repetitive inspections required by paragraph A. of this AD. \n\n\tD.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\tE.\tSpecial 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. \n\n\tF.\tThe modification shall be done in accordance with Boeing Service Bulletin 747- 26-2162, dated September 20, 1990. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. \n\n\tAirworthiness Directive 91-20-06 supersedes AD 89-22-03, Amendment 39-6353. \n\tThis amendment (39-8040, AD 91-20-06) becomes effective on November 7, 1991.
92-17-05: 92-17-05 DASSAULT AVIATION: Amendment 39-8334. Docket No. 92-NM-25-AD. Applicability: Model Fan Jet Falcon Basic D, E, and F series airplanes; and Model Mystere- Falcon 20-C5, D5, E5, and F5 airplanes; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of these airplanes, accomplish the following: (a) Incorporate a revision into the FAA-approved maintenance inspection program that provides for inspection of the Significant Structural Items defined in Dassault Aviation Service Bulletin FJF-00-26 (FJF-730), Revision 1, dated December 12, 1990, at the later of the times specified in subparagraph (a)(1) or (a)(2): (1) Prior to the accumulation of 20,000 landings or 30,000 hours time-in-service, whichever occurs first; or (2) Within 6 months after the effective date of this AD. (b) Report the results, positive or negative, of each inspection required by paragraph (a) of this AD to Dassault Aviation, in accordance with the instructions in Dassault Aviation Service Bulletin FJF-00-26 (FJF-730), Revision 1, dated December 12, 1990. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (c) Cracked structures detected during the inspections required by paragraph (a) of this AD must be repaired or replaced, prior to further flight, in accordance with the instructions in Dassault Aviation Service Bulletin FJF-00-26 (FJF-730), Revision 1, dated December 12, 1990, or in accordance with other data meeting the certification basis of the airplane which is approved by the FAA or by the French Direction G n rale de l'Aviation Civile (DGAC). (d) 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, Transport Airplane 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. (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) The inspections, repairs, and replacement shall be done in accordance with Dassault Aviation Service Bulletin FJF-00-26 (FJF-730), Revision 1, dated December 12, 1990. 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 fromFalcon Jet Corporation, Customer Support Department, Teterboro Airport, Teterboro, New Jersey 07608. 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., 7th Floor, Suite 700, Washington, DC. (g) This amendment becomes effective on September 28, 1992.
2018-25-09: We are adopting a new airworthiness directive (AD) for all CFM International S.A. (CFM) LEAP-1B21, -1B23, -1B25, -1B27, -1B28, - 1B28B1, -1B28B2, -1B28B2C, -1B28B3, -1B28BBJ1, and -1B28BBJ2 turbofan engines. This AD requires removing certain electronic engine control (EEC) system operation (OPS) and engine health monitoring (EHM) software and installing versions eligible for installation. This AD was prompted by six aborted takeoffs on the similarly designed CFM LEAP-1A model turbofan engine after those engines did not advance to the desired takeoff fan speed due to icing in the pressure sensor line. We are issuing this AD to address the unsafe condition on these products.
99-26-20 L: 99-26-20 MD HELICOPTERS INC.: Docket No. 99-SW-89-AD. \n\n\tApplicability: Model MD-900 helicopters, with Main Rotor Upper Hub (hub) Assembly, part number (P/N) 900R2101006-105 or 900R2101006-107, installed, certificated in any category. \n\n\tNOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent failure of the hub assembly, loss of drive to the main rotor, and subsequent loss of control of the helicopter, accomplish the following: \n\n\t(a)\tFor the hub assembly, P/N 900R2101006-107, \n\n\t\t(1)\tWithin 6 hours time-in-service (TIS) or before flight after January 31, 2000, whichever occurs first, visually inspect the hub assembly drive plate attach flange (flange) for a crack and determine the torque of each flange attach nut (nut) in accordance with the Accomplishment Instructions, Part I, paragraph 2.A., steps (1) through (7) of MD Helicopter Inc. Service Bulletin SB900-072, dated December 10, 1999 (SB). If a crack is found, before further flight, remove and replace the hub assembly with an airworthy hub assembly. \n\n\t\t(2)\tWithin 25 hours TIS or before flight after January 31, 2000, whichever occurs first, conduct the Accomplishment Instructions, Part II, paragraph 2.B., steps (1) through (6), (8),and (9) of the SB. If a crack is found, before further flight, remove and replace the hub assembly with an airworthy hub assembly. \n\n\t(b)\tFor the hub assembly, P/N 900R2101006-105, \n\n\t\t(1)\tWithin 6 hours TIS or before flight after January 31, 2000, whichever occurs first, visually inspect the flange for a crack and determine the torque of each nut in accordance with the Accomplishment Instructions, Part I, paragraph 2.A., steps (1) through (7) of the SB. \n\n\tNOTE 2: The SB effectivity does not include hub assembly, P/N 900R2101006-105; however, for the requirements of this AD, certain provisions of the SB do apply to this P/N . \n\n\t\t(2)\tIf any nut has less than 180 inch pounds (20.34 Nm) of torque, before further flight, remove the hub assembly, disassemble, inspect, and reassemble in accordance with the procedures in paragraph (b)(4) of this AD. If a crack is detected, before further flight, remove and replace the hub assembly with an airworthy hub assembly. \n\n\t\t(3)\tWithin25 hours TIS or before flight after January 31, 2000, whichever occurs first, remove and visually inspect the hub assembly as follows: \n\n\t\t\t(i)\tIf present, remove sealant from the drive plate attachment to the hub assembly. \n\n\t\t\t(ii)\tMark the main rotor hub holes, bolts, and nuts to correspond with the drive plate hole numbers. (See Figure 1.) \n\n\t\t\t(iii)\tRemove the main rotor drive plate (drive plate) assembly and anti-fretting ring (fretting buffer). \n\n\t\t\t(iv)\tInspect drive plate to rotor hub assembly mating surfaces and the fretting buffer for fretting. \n\n\t\t\t(v)\tUsing paint stripper (C313 or equivalent) and cleaning solvent (C420 or equivalent), remove the paint from the upper mating surface of the hub assembly to enable an accurate visual inspection of the drive plate attachment bolt hole (bolt hole) area for cracking (Figure 1). Ensure the paint stripper and solvent DO NOT contaminate the upper bearing and upper grease seal areas. \n\n\t\t\t(vi)\tUsing a 10-power or highermagnifying glass and bright light, inspect the mating surface area and the area around and inside the 10 bolt holes of the hub assembly for a crack. If a crack is found, prior to further flight, replace the hub assembly with an airworthy hub assembly. \n\n\t\t\t(vii)\tIf no crack is found, remove fretting from the mating surfaces of the hub assembly and the drive plate assembly, reassemble, fillet seal (C211 or equivalent) the surface of the drive plate to fretting buffer to hub assembly mating lines, and seal all exposed unpainted upper surfaces of the hub assembly. \n\n\t\t\t(viii)\tReinstall the main rotor drive plate using 10 new sets of replacement attachment hardware. Torque the nuts to 160 inch pounds above locknut locking/run-on torque in the sequence shown (Figure 1). Record in the rotorcraft logbook, or equivalent record, the locknut locking/run-on torque for each nut. \n\n\t\t\t(ix)\tAfter the next flight, verify that the torque on each of the 10 nuts is at least 160 inch pounds above the locknut locking/run-on torque (minimum torque). Retorque as required without loosening nuts \n\n\t\t\t(x)\tThereafter, at intervals of at least 4 hours TIS, not to exceed 6 hours TIS, verify that the torque of each of the 10 nuts is at least the minimum torque. Retorque as required without loosening nuts. This torque verification is no longer required after the torque on each of the 10 nuts has stabilized at the minimum torque 160 inch pounds for each nut during two successive torque verifications. \n\n\t(c)\tAn 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, Los Angeles Aircraft Certification Office, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. \n\n\tNOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles Aircraft Certification Office. \n\n\t(d)\tIf any nut torque is below minimum torque and no hub assembly crack is found before disassembly inspection, after retorque in accordance with the applicable Maintenance Manual, a special flight permit for one flight below 100 knots indicated airspeed may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished. \n\n\t(e)\tCopies of the applicable service information may be obtained from MD Helicopters Inc., Attn: Customer Support Division, 5000 E. McDowell Rd., Mail Stop M615-GO48, Mesa, Arizona 85215-9797, telephone 1-800-388-3378 or 480-891-6342, datafax 480-891-6782. This information may be examined at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas. \n\n\t(f)\tEmergency Priority Letter AD 99-26-20, issued December 17, 1999, becomes effective upon receipt. \n\n\n\t\t\t\t\tFIGURE 1\n \t\t\t\t\t 99-26-20
2006-06-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and A330-300 series airplanes; and Model A340-200 and -300 series airplanes. This AD requires repetitive detailed inspections for discrepancies of the inboard and outboard actuator fittings of the aileron servo controls, corrective actions if necessary, and eventual replacement of all the attachment bolts of the aileron servo controls. This AD results from several cases of bushing migration on the inboard and outboard actuator fittings of the aileron servo controls; in one case the bushing had migrated completely out of the actuator fitting and the fitting was cracked. We are issuing this AD to prevent rupture of the inboard and outboard actuator fittings of the aileron servo controls, which could result in airframe vibration and consequent reduced structural integrity of the airplane.
59-13-01: 59-13-01 ALLISON: Applies to Models 501-D13 and -D13A Engines. Compliance required as indicated. Seven recent cases of spalling of the propeller shaft roller bearing on Allison 501-D13 engines necessitates a continuity check using a probe be made of the reduction gear magnetic plug at least every 10 hours on engine installations not modified in accordance with Allison Commercial Engine Bulletin 72-74 and Lockheed Bulletin SB 262. This check is necessary due to high bearing loads caused by propeller during certain aircraft flight conditions. If metal chips are found as described in Allison Maintenance Manual, section 72-0, paragraph 8B, page 219, remove gearbox. This supersedes AD 59-11-01.
89-16-06: 89-16-06 BRITISH AEROSPACE (BAe) PLC: Amendment 39-6266. Applicability: Jetstream Model 3101 (all serial numbers) airplanes which have Kit 3279A embodied as part of Omnibus Modification 7380, certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To assure operation of the airplane within the design airspeed limitations, accomplish the following: (a) Modify the pilot's and copilot's operating limitations placards and revise the Airplane Flight Manual in accordance with British Aerospace Alert Service Bulletin 11-A-JA880140, dated February 23, 1988. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to British Aerospace, Inc., Technical Librarian, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6266, AD 89-16-06) becomes effective on August 29, 1989.