Results
96-25-14: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -30, and -40 series airplanes, and KC-10 (military) series airplanes, that requires repetitive high frequency eddy current (HFEC) inspections to detect cracks in the number 4 banjo fitting on the rear spar of the vertical stabilizer, and repair and modification of the vertical stabilizer, if necessary. It also requires the installation of a modification as terminating action for the repetitive inspections. This amendment is prompted by reports of failed attach bolts and cracking found in the area of the number 4 banjo fitting, which were caused by higher than normal operating stresses. The actions specified by this AD are intended to prevent reduction in the structural integrity of this fitting due to failed bolts and cracking.
96-25-08: This amendment adopts a new airworthiness directive (AD), applicable to all de Havilland Model DHC-7 series airplanes, that requires performing a review of the airplane maintenance records to determine if any insulation blankets have been repaired or changed during service, and various follow-on actions, if necessary. This amendment is prompted by reports of corrosion forming on areas of the airplane structure where black film thermal insulation blankets are used. The actions specified by this AD are intended to prevent such corrosion, which could result in degradation of the structural capability of the airplane fuselage and consequent sudden loss of cabin pressure.
2021-08-01: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) RB211 Trent 768-60, RB211 Trent 772-60, and RB211 Trent 772B-60 model turbofan engines. This AD was prompted by maintenance that resulted in damage to certain low-pressure compressor (LPC) blades, resulting in increased susceptibility to cracking in the LPC blade root. This AD requires initial and repetitive inspections of the blade root of certain LPC blades and re-lubrication of the LPC blades and LPC disk. Depending on the results of the inspections, this AD requires replacement of the LPC blades. As a terminating action to the inspection and re-lubrication requirements, this AD requires restoration of the LPC blade as well as examination and re-lubrication of the LPC disk. The FAA is issuing this AD to address the unsafe condition on these products.
92-09-08: 92-09-08 FOKKER: Amendment 39-8233. Docket No. 91-NM-127-AD. Applicability: Model F28 Mark 0100 series airplanes equipped with Smiths Industries Combined Processor/Totaliser (CPT) units having fuel quantity indication in pounds, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent inaccurate presentation of fuel quantity, accomplish the following: (a) Within 120 days after the effective date of this AD, remove the CPT unit, modify the airplane's electrical wiring connection for the CPT unit, and install a new CPT unit having a modified connector which will mate with the newly-installed connector, in accordance with Fokker Service Bulletin F100-28-015, dated January 30, 1991. (b) Subsequent to accomplishing the requirements of paragraph (a) of this AD, perform the operational tests in accordance with Fokker Service Bulletin F100-28-015, dated January 30, 1991. (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. NOTE: The request should 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 modification shall be done in accordance with Fokker Service Bulletin F100-28-015, dated January 30, 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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 June 11, 1992.
2021-08-11: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of one or both roll control input modules (RCIMs) being incorrectly installed. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate certain aircraft maintenance manual (AMM) tasks. The FAA is issuing this AD to address the unsafe condition on these products.
96-25-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires repetitive visual inspections and end-float checks of the ram air turbine (RAT), and replacement of the RAT, if necessary. This amendment requires installation of a modified RAT, which constitutes terminating action for the currently required inspections. This amendment is prompted by the development of a modification of the RAT that positively addresses the unsafe condition. The actions specified by this AD are intended to prevent the RAT from breaking away from its support leg, which could damage the airplane structure and systems, and could injure ground personnel.
77-14-17 R1: 77-14-17 R1 DORNIER GmbH: Amendment 39-2966 as amended by Amendment 39-4934. Applies to all Model Do 27 and Do 28 series (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To detect defective DORNIER fuel and oil hoses manufactured to specification LN9226 and to prevent possible engine failure or sudden seizure of an engine, accomplish the following: (a) Within the next 10 hours time-in-service (TIS) after the effective date of this Airworthiness Directive (AD), or within the next 25 hours TIS since the last inspection in accordance with AD 77-14-17, whichever occurs first, and every 25 hours thereafter until attaining more than 50 hours TIS on each hose, visually inspect each of the DORNIER fuel and oil hoses, manufactured to specification LN9226 in the first quarter of 1970 and thereafter, for defects in accordance with paragraph 1 of DORNIER Service Bulletin No. 1059-0000, dated September 25, 1975, or an FAA equivalent method. If the specification of a particular hose or its date of manufacture is unknown, the inspections required by this paragraph must be accomplished for that hose. (b) If a defective hose is found during any inspection required by paragraph (a) of this AD, before further flight, replace the defective hose with a serviceable DORNIER or TSO-C53a, Type C hose. (c) The repetitive inspections required on each individual fuel and oil hose by paragraph (a) are not required: (1) On any installed serviceable TSO-C53a, Type C hose, or (2) On any DORNIER hose which is found serviceable after the second sequential 25 hour TIS inspection, or (3) On any DORNIER hose which has more than 50 hours TIS and remains serviceable in accordance with the inspection required by paragraph (a) of this AD. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) Equivalent means of compliance may be used, if approved, by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. Amendment 39-2966 became effective on July 28, 1977. This Amendment 39-4934 becomes effective on March 22, 1985.
93-07-12: 93-07-12 FAIRCHILD AIRCRAFT (formerly Swearingen Aircraft Corporation): Amendment 39-8544. Docket No. 91-CE-36-AD. Supersedes AD 74-24-02, Amendment 39-2529. Applicability: The following model and serial number airplanes, certificated in any category: Models Serial Numbers SA226-T, SA226-T(B) SA226-AT, and SA226-TC all serial numbers SA227-TT TT421 through TT527 SA227-AC AC406, AC415, AC416, AC420 through AC509, and AC511 through AC530 SA227-AT AT423 through AT524 Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent failure of the horizontal stabilizer rear spar, which could result in loss of control of the airplane, accomplish the following: (a) Within the next 50 hours time-in-service (TIS), unless already accomplished within the last 450 hours TIS, and thereafter at intervals not to exceed 500 hours TIS until the modification required by paragraph (b) of this AD is accomplished,dye penetrant inspect the horizontal stabilizer rear spar at the left and right outboard elevator hinge bracket attachment for cracks in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Aircraft Service Bulletin (SB) 226-55-005, Issued: August 15, 1985, Revised: January 7, 1991; or Fairchild Aircraft SB 227-55-002, Issued: August 15, 1985, Revised: October 13, 1988, as applicable. (b) If cracks are found in the horizontal stabilizer rear spar, prior to further flight, repair any crack in accordance with a repair scheme obtained from the manufacturer through the Manager, Fort Worth Airplane Certification Office, at the address specified in paragraph (f) of this AD. (c) Within the next 2,200 hours TIS, modify the outboard hinge in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Aircraft SB 226-55-005, Issued: August 15, 1985, Revised: January 7, 1991; or Fairchild Aircraft SB 227-55-002, Issued: August 15, 1985, Revised: October 13,1988, as applicable. (d) The accomplishment of the modification required by paragraph (c) of this AD is considered terminating action for the repetitive inspection requirement of this AD. This modification may be accomplished at any time prior to 2,200 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, 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may beobtained from the Fort Worth Airplane Certification Office. (g) The inspections and modification required by this AD shall be done in accordance with Fairchild Aircraft Service Bulletin 226-55-005, Issued: August 15, 1985, Revised: January 7, 1991; or Fairchild Aircraft Service Bulletin 227-55-002, Issued: August 15, 1985, Revised: October 13, 1988, 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 (39-8544) supersedes AD 74-24-02, Amendment 39-2529, which superseded AD 74-18-14, Amendment 39-1950. (i) This amendment becomes effective on May 28, 1993.
2021-07-10: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a report that some piccolo ducts for the wing anti-ice system have bleed holes that do not conform to requirements. This AD requires, depending on airplane configuration, inspection for the presence of affected wing anti-ice system piccolo ducts and corrective actions, or replacement of affected piccolo ducts with new piccolo ducts. The FAA is issuing this AD to address the unsafe condition on these products.
96-24-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing 747-400 series airplanes in the "combi" configuration. This action requires replacing the decompression panels that are located in the smoke barrier between the passenger and main deck cargo compartment, with new panels of an improved design. This amendment is prompted by reports indicating that normal pressurization cycles are causing premature tearing or opening of these decompression panels. The actions specified in this AD are intended to prevent increased airflow in the cargo compartment caused by the tearing or opening of these panels; this condition, if not corrected, could result in delayed fire detection and reduced effectiveness of the cargo compartment fire suppression system.
2009-04-07: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: An A330 aircraft experienced a sudden [uncommanded] nose down order [event] while in cruise. This order was preceded by an automatic autopilot disconnection and triggering of the "NAV IR1 FAULT'' Electronic Centralised Aircraft Monitor (ECAM) Caution. Investigations highlighted that at time of the event the Air Data Reference 1 (ADR) part of ADIRU1 [Air Data Inertial Reference Unit] was providing erroneous and temporary wrong parameters in a random manner. This abnormal behaviour of the ADR1 led to several consequences such as unjustified stall and over speed warnings, loss of attitude information on Captain Primary Flight Display (PFD) and several ECAM warnings. Among the abnormal parameters, the provided Angle of Attack (AoA) value was such that the flight control computers commanded a sudden nose down aircraft movement, which constitutes an unsafe condition. * * * * * * * * These anomalies could result in high pilot workload, deviation from the intended flight path, and possible loss of control of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2021-04-11: The FAA is superseding Airworthiness Directive (AD) 2020-01- 10, which applied to certain Airbus SAS Model A350-941 airplanes. AD 2020-01-10 required installing flight control and guidance system (FCGS) software (SW) X11 Standard (STD). This AD retains the requirements of AD 2020-01-10, requires modifying the electrical power supply of the air generation system (AGS) ram air outlet door actuators, and expands the applicability by adding airplanes, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by the development of a modification that forces the AGS ram air outlet doors to be flush in cases of total engine flameout or loss of the main electrical supply. Because of this additional modification, certain airplanes that were excluded from the applicability of AD 2020-01-10 are included in the applicability of this AD. The FAA is issuing this AD to address the unsafe condition on these products.
76-09-06: 76-09-06 SIAI-MARCHETTI: Amendment 39-2595. Applies to Model S205 airplanes, S/N 5-406 and below, and Model S208 airplanes, S/N 4-64 and below, certificated in all categories. Compliance is required as indicated. To prevent a possible loss of aileron control, accomplish the following: (a) Within 10 hours time in service after the effective date of this AD, unless already accomplished within the preceding 15 hours time in service and thereafter, at intervals not to exceed 25 hours time in service from the last inspection, visually inspect the rear wing spar for cracks in accordance with paragraph (a) of the 'INSTRUCTIONS" section of SIAI Marchetti Service Bulletin No. 205B42, dated January 3, 1976, or an FAA-approved equivalent. (b) If a crack is found during an inspection required by paragraph (a) of this AD, before further flight, repair and reinforce the rear wing spar adjacent to the inboard and outboard aileron hinge attachments in accordance with paragraphs (c) and (d) of the "INSTRUCTIONS" section of SIAI Marchetti Service Bulletin No. 205B42, dated January 3, 1976, or an FAA- approved equivalent, except that, for SIAI Marchetti Model S205 airplanes, S/N's 101 through 222, 224, 228, 229, 231, 232, and 233, the reinforcement provisions of paragraph (c) of the Service Bulletin need not be accomplished. (c) The repetitive inspections required by paragraph (a) of this AD may be discontinued after the repair and reinforcement required by paragraph (b) of this AD is accomplished. This amendment becomes effective May 10, 1976.
2021-07-12: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD was prompted by a reassessment of the flight control system. This AD requires modification of the cyclic stick, 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.
96-23-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires inspections to detect disbonding, corrosion, and cracking at the longitudinal rows of fasteners in the bonded skin panels in section 41 of the fuselage, and repair, if necessary. This amendment is prompted by a report of skin cracking due to disbonding of the internal doubler of the cracked skin panels. The actions specified in this AD are intended to prevent rapid decompression of the airplane due to disbonding and subsequent cracking of the skin panels.
2021-07-06: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a determination that certain airplanes have outdated magnetic variation (MagVar) tables inside navigation systems. This AD requires revising the existing airplane flight manual (AFM) to update the Flight Management System (FMS) and Inertial Reference System (IRS) limitations. The FAA is issuing this AD to address the unsafe condition on these products.
76-17-07: 76-17-07 BOEING: Amendment 39-2706. Applies to Boeing Model 727-100 series airplanes certificated in all categories with static port heater circuits deactivated. Compliance required as indicated unless already accomplished. \n\tTo prevent the loss of altitude and airspeed reference due to a small amount of water freezing in the static port system, accomplish either of (1) or (2) below: \n\t(1)\tWithin the next 1,000 hours time in service after the effective date of this AD reactivate the static port heater circuits to the original FAA approved Boeing 727-100 configuration; or \n\t(2)\tWithin the next 2,000 hours time in service after the effective date of this AD replace the deactivated heater assembly, P/N 10-60723-1, with elbow fitting MS21908D6 in accordance with Boeing Service Bulletin 727-34-95 dated September 3, 1976, or later FAA approved service bulletins, and enlarge the static port sensing holes from .047 inch diameter to .125 inch diameter in accordance with Boeing ServiceBulletin 727-34-94 (to be released) or later FAA approved service bulletins. \n\tNotwithstanding the provisions of the above paragraph (1) the heater elements in one static system may be inoperative provided the aircraft is not flown in icing or precipitation conditions. \n\tBoeing 727-100 airplanes already incorporating Boeing Service Bulletin 727-25-42, Revision 1, dated March 4, 1968, with elbow fitting MS21908D6 and Boeing Service Bulletin 727-34-57 dated April 7, 1968, enlarging the static sense holes are in compliance with this AD. \n\tEquivalent modifications may be 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. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington.\n \n\tThis amendment becomes effective October 1, 1976.
96-22-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe series 1000A and Model Hawker 1000 airplanes, that requires modifications of the thrust reversers. This amendment is prompted by a review of the certification analysis of the thrust reversers and by testing of the thrust reversers, which indicated that additional design features are necessary to prevent failure of the driver link and the inadvertent deployment of a thrust reverser during flight. The actions specified by this AD are intended to prevent inadvertent deployment of a thrust reverser during flight, which could result in reduced controllability of the airplane.
96-22-12: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Corporation (Raytheon) Models 1900C, 1900D, and 2000 airplanes. This action requires inspecting (one-time) the fuel filter assemblies to detect any bypass valve that is glued shut. If a bypass valve is glued shut, the AD requires replacing the associated fuel filter assembly. Three in-flight occurrences in which the low fuel pressure light illuminated prompted this action. In each of the instances, a bypass valve on the affected airplane engine was glued shut with anaerobic thread lock adhesive and when the fuel filter became clogged, proper fuel flow to the engine was not obtained. The actions specified by this AD are intended to prevent lack of fuel to the engine and eventual engine shutdown caused by a clogged fuel filter and a contaminated fuel filter bypass valve.
93-07-04: 93-07-04 BRITISH AEROSPACE: Amendment 39-8536. Docket 92-NM-189-AD. Applicability: Model ATP series airplanes; serial numbers 2001 through 2049, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent possible loss of integrity and security of the flap drive system, accomplish the following: (a) Within 14 days after the effective date of this AD, perform a one-time general visual inspection of the primary flap drive torque tubes to ensure that the four bolt and nut assemblies on the splined flanged-coupling assembly on the right gearbox drive at station 0 have split pins installed, in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. (1) If split pins are installed, no further action is necessary. (2) If any split pin is missing, accomplish the requirements of both paragraphs (a)(2)(i) and (a)(2)(ii) of this AD: (i) Prior to further flight, check tighten each of the four bolts to 8 to 10 foot pounds torque. Repeat this check tightening thereafter at intervals not to exceed 14 days. (ii) Within 6 months after the effective date of this AD, install split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. Installation of these split pins constitutes terminating action for the inspections and check tightening requirements of this paragraph. (b) Installation of split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992, constitutes terminating action for the requirements of paragraph (a) of this AD. (c) 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. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the 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 inspection and installation shall be done in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 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 Jetstream Aircraft, Inc., Librarian for Service Bulletins, P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. 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. (f) This amendment becomes effective on May 10, 1993.
2021-07-14: The FAA is adopting a new airworthiness directive (AD) for all Yabora Industria Aeronautica S.A. Model EMB-135 and EMB-145 airplanes. This AD was prompted by a report involving disconnection of a side arm strut from the right main landing gear (MLG); a subsequent investigation found that the side arm strut lower bearing was installed inverted on the airplane. This AD requires doing a general visual inspection of the right and left MLG to verify certain conditions and doing all applicable on-condition actions, as specified in an Agencia Nacional de Aviacao Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
91-23-12: 91-23-12 LOCKHEED: Amendment 39-8081. Docket No. 91-NM-77-AD. Applicability: Model L-1011 series airplanes, equipped with BFGoodrich brake part numbers identified in paragraph (a) of this AD, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the loss of main landing gear braking effectiveness, accomplish the following: (a) Within 180 days after the effective date of this AD, inspect the brake part numbers shown below for wear. Any brake worn more than the maximum wear limit specified below must be replaced, prior to further flight, with a brake within this limit. Type Certificated Model Designation Common Model Designation Maximum GTOW Brake Part No. Maximum Wear Limit (inches) L-1011-385-1 (-1) 430,000 2-1195-1 2.10 (-1) 430,000 2-1195-5 2.10 (-1) 430,000 2-1195-6 2.10 (-1) 430,000 2-1195-7 2.10 (-1) 430,000 2-1195-8 2.10 (-1) 430,000 2-1367 3.00 (-1) 430,000 2-1367-1 3.00 (-1) 430,000 2-1367-2 3.00 (-40) 440,000 2-1195-1 2.10 (-40) 440,000 2-1195-5 2.10 (-40) 440,000 2-1195-6 2.10 (-40) 440,000 2-1195-7 2.10 (-40) 440,000 2-1195-8 2.10 (-40) 440,000 2-1367 3.00 (-40) 440,000 2-1367-1 3.00 (-40) 440,000 2-1367-2 3.00 (-50) 450,000 2-1367-3 2.60 (-50) 450,000 2-1367-4 2.60 (-50) 450,000 2-1367-5 2.60 L-1011-385-1-14 (-100,-150,-200) 466,000 2-1367-3 2.60 (-100,-150,-200) to 2-1367-4 2.60 (-100,-150,-200) 474,000 2-1367-5 2.60 (-250) 510,000 2-1367 3.00 (-250) 510,000 2-1367-1 3.00 (-250) 510,000 2-1367-2 3.00 L-1011-385-1-15 (-100,-150,-200) 466,000 2-1367-3 2.60 (-100,-150,-200) to 2-1367-4 2.60 (-100,-150,-200) 474,000 2-1367-5 2.60 (-250) 510,000 2-1367 3.00 (-250) 510,000 2-1367-1 3.00 (-250)510,000 2-1367-2 3.00 L-1011-385-3 (-500) 496,000 2-1367 3.00 (-500) to 2-1367-1 3.00 (-500) 516,000 2-1367-2 3.00 NOTE: Lockheed Service Bulletin 093-32-253, dated March 29, 1991, contains additional information concerning Model L-1011 brake configurations. (b) Within 180 days after the effective date of this AD, incorporate the maximum brake wear limits specified in paragraph (a) of this AD into the FAA-approved maintenance inspection program. (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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. (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. This amendment (39-8081, AD 91-23-12) becomes effective on December 9, 1991.
96-21-10: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
96-21-01: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 series airplanes, that requires either replacement or modification of the hydraulic damper assembly. This amendment is prompted by reports indicating that insufficient damping of the hydraulic shimmy damper in the main landing gear (MLG) can allow high torsional vibration to occur. The actions specified by this AD are intended to prevent such vibration, which can damage the MLG assembly and lead to its collapse.
93-04-02: 93-04-02 ROCKWELL INTERNATIONAL/COLLINS AVIATION DIVISION: Amendment 39-8504. Docket No. 93-CE-18-AD. Applicability: TDR-94D Mode S transponders, P/N CPN 622-9210-002, installed on, but not limited to the following, certificated in any category: Aerospatiale ATR-42 and ATR-72 series airplanes Saab 340A and 340B airplanes Short Model SD3-60 airplanes de Havilland DHC-7 and DHC-8 series airplanes British Aerospace ATP airplanes Gulfstream G-II, G-III, and G-IV series airplanes Dassault Mystere-Falcon 50, Mystere-Falcon 200, and Mystere-Falcon 900 airplanes Canadair Challenger CL-601 airplanes British Aerospace HS 125-700A airplanes Beechcraft 300 series airplanes Compliance: Required as indicated, unless already accomplished. To prevent a mid-air collision or a near-miss situation caused by failure of these Mode S transponders, accomplish the following: (a) Within the next 10 calendar days after theeffective date of this AD, fabricate a placard with the following words in letters at least 0.10-inch in height and install this placard within the pilot's clear view on the instrument panel: "OPERATION OF TCAS II IN ANY MODE OTHER THAN THE "TA ONLY" MODE IS PROHIBITED." (b) Within the next 6 calendar months after the effective date of this AD, modify the software of the Mode S transponders in accordance with the Accomplishment Instructions section of Collins Service Bulletin TDR-94/94D-34-6, Revision 2, dated September 21, 1992. The placard required by paragraph (a) of this AD is no longer required after this modification is incorporated. (c) If parts for the above modification are not available, the airplane operator may comply with the placard requirement of paragraph (a) of this AD until the modification is incorporated based upon a schedule established by the manufacturer through the Atlanta Aircraft Certification Office. (d) Special flight permits may be issuedin 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) An alternative method of compliance or adjustment of the compliance times 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. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (f) The modification required by this AD shall be done in accordance with Collins Service Bulletin TDR-94/94D-34-6, Revision 2, dated September 21, 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 Rockwell International/Collins General Aviation Division, 1100 West Hibiscus Boulevard, Melbourne, Florida 32901. 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., 7th Floor, suite 700, Washington, DC. (g) This amendment becomes effective on March 26, 1993.