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89-03-02: 89-03-02 FOKKER: Amendment 39-6121. Applicability: Model F-28 series airplanes, Serial Number 11003 through 11231, 11991, and 11992, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a potential fire hazard in the cockpit, accomplish the following: A. Within 60 days after the effective date of this AD, relocate the instrument lighting ballast transformers from the glareshield panel and the right-hand cockpit sidewall to the left-hand cockpit sidewall, in accordance with Fokker Service Bulletin No. F28/33-34, dated June 1, 1988. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. 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 documents from the manufacturer may obtain copies upon request to Fokker Aircraft, USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6121, AD 89-03-02) becomes effective March 6, 1989.
97-04-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires modification of the aileron centering spring and trim mechanism. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent jamming of the aileron control system during flight due to fracturing of the springs in the aileron centering units; this condition, if not corrected, could result in reduced lateral control of the airplane.
97-03-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and Model DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires modification of the girt and firing lanyard stowage. This amendment is prompted by reports of in-cabin inflation of certain evacuation slides due to the impingement of the galley service cart on the slide girt and firing lanyard. The actions specified by this AD are intended to prevent inadvertent inflation of the evacuation slides inside the cabin, which could contribute to injury of passengers and/or flightcrew in the passenger cabin.
91-20-05: 91-20-05 BRITISH AEROSPACE: Amendment 39-8039. Docket No. 91-NM-110-AD. Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of cabin pressurization, accomplish the following: (a) For airplanes operated to a maximum of 7.5 pounds per square inch (psi) cabin pressure differential: Prior to the accumulation of 24,000 landings, or within 3,000 landings after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 3,200 landings; perform a visual inspection of the skin and cleats at the front and rear extremities of the twelve stiffeners to detect cracks, in accordance with British Aerospace Alert Service Bulletin 53-A-PM5990, Issue 1, dated January 7, 1991. (b) For airplanes modified for operation to a maximum of 8.2 psi cabin pressure differential: Prior to the accumulation of 16,000 landings, or within 2,000 landings after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 2,400 landings; perform a visual inspection of the skin and cleats at the front and rear extremities of the twelve stiffeners to detect cracks, in accordance with the British Aerospace Alert Service Bulletin 53-A-PM5990, Issue 1, dated January 7, 1991. (c) If skin cracks are found, prior to further flight, repair in accordance with a procedure approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. If cleat cracks are found, prior to further flight, replace cracked cleats by installing a new part having post-Modification PM5629 Part (a) configuration. (d) For all airplanes: Prior to the accumulation of 85,000 landings, install Modification PM5629 Part (a) in accordance with British Aerospace Alert Service Bulletin 53-A-PM5990, Issue 1, dated January 7, 1991. (e) Installation of Modification PM5629 Part(a), in accordance with British Aerospace Alert Service Bulletin 53-A-PM5990, Issue 1, dated January 7, 1991, constitutes terminating action for the repetitive inspections required by paragraphs (a) and (b) of this AD. (f) 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. (g) 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. (h) The inspection, repair, and installation requirements shall be done in accordance with British Aerospace Alert Service Bulletin 53-A-PM5990, Issue 1, dated January 7, 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-8039, AD 91-20-05) becomes effective on November 7, 1991.
2021-08-19: The FAA is superseding Airworthiness Directive (AD) 2021-02- 19, which applied to certain The Boeing Company Model 787-8, -9, and - 10 airplanes. AD 2021-02-19 required repetitive general visual inspections for disengaged or damaged decompression panels of the bilge barriers located in the forward and aft cargo compartments, reinstallation of disengaged but undamaged panels, and replacement of damaged panels. This AD was prompted by reports of multiple incidents of torn decompression panels found in the bilge area, and the determination that additional airplanes are subject to the unsafe condition. This AD retains the requirements of AD 2021-02-19 and revises the applicability by including additional airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
91-23-05: 91-23-05 FOKKER: Amendment 39-8074. Docket No. 91-NM-115-AD. Applicability: Model F-28 Mark 0100 series airplanes; Serial numbers 11244 through 11306, 11308, 11310, 11312, 11313, 11314, 11316, and 11318; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced controllability of the airplane, accomplish the following: (a) Within 6 months after the effective date of this AD: (1) Replace all aileron, elevator, and rudder servomotors, P/N 622-7925-302, with modified servomotors, P/N 622-7925-303, in accordance with Fokker Service Bulletin F100-22-015, dated November 16, 1990; and (2) Replace all aileron and rudder servomounts, P/N 622-7926-302; and elevator servomounts, P/N 622-8069-302; with modified servomounts, P/N 622-7926-303 and 622-8069-303, respectively, in accordance with Fokker Service Bulletin F100-22-018, Revision 1, dated January 24, 1991. (b) 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. (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. (d) The replacement requirements shall be done in accordance with Fokker Service Bulletin F100-22-015, dated November 16, 1990, and Fokker Service Bulletin F100-22-018, Revision 1, dated January 24, 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 S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-8074, AD 91-23-05) becomes effective on December 17, 1991.
2021-08-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that a welding quality issue has been identified in the gimbal joint of the air bleed duct located at each wing-to-pylon interface; the inner ring of a gimbal had deformed to an oval shape, which could lead to cracking caused by direct contact between metal parts. This AD requires replacing affected bleed duct assemblies and bleed gimbals at the wing-to-pylon interface with a serviceable part, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
97-02-15: This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Helicopter Company (Robinson) Model R44 helicopters, that currently requires an adjustment to the low RPM warning unit threshold to increase the revolutions-per-minute (RPM) at which the warning horn and caution light activate, and revisions to the R44 Rotorcraft Flight Manual that prohibit flight with the throttle governor (governor) selected off, except in certain situations. This amendment requires the same compliance actions required by the existing AD, and corrects the applicability section of the existing AD. This amendment is prompted by the need to expand the applicability statement of this AD to include all Robinson Model R44 helicopters. The actions specified by the proposed AD are intended to minimize the possibility of pilot mismanagement of the main rotor (M/R) RPM, which could result in unrecoverable M/R stall and subsequent loss of control of the helicopter.
2021-08-03: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) airplanes; Model CL-600-2C11 (Regional Jet Series 550) airplanes; Model CL-600-2D15 (Regional Jet Series 705) airplanes; Model CL-600- 2D24 (Regional Jet Series 900) airplanes; and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that a new or more restrictive airworthiness limitation is necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate a new or more restrictive airworthiness limitation. The FAA is issuing this AD to address the unsafe condition on these products.
97-02-02: This amendment adopts a new airworthiness directive (AD) that applies to Fairchild Aircraft, Inc. (Fairchild) SA26, SA226, and SA227 series airplanes. This action requires applying torque to the control column pitch bearing attaching nuts, inspecting for any looseness or movement of the bearing assembly, and inspecting the elevator control rod end bearing retainer/dust seals for creasing. If either of these problems are evident, this action requires replacing these parts, as well as installing a new bolt and washer to the elevator control rod end bearing assembly at the walking beam connection. Reports of Fairchild SA227 series airplanes losing pitch control in-flight prompted this action. The actions specified by this AD are intended to prevent loss of pitch control which, if not corrected, could result in loss of the airplane.
97-01-05: This amendment adopts a new airworthiness directive (AD) that is applicable to Williams International, L.L.C. Model FJ44-1A turbofan engines. This action requires initial and repetitive eddy current inspections (ECI) for possible cracks in high pressure turbine (HPT) disk blade retention posts. In addition, this AD requires the installation of advanced design HPT disks as terminating action to the inspection requirements of this AD. This amendment is prompted by two incidents of HPT disk blade retention post separations. The actions specified in this AD are intended to locate possible cracks in HPT disk blade retention posts, thereby preventing the separation of these posts and the liberation of the turbine blades that they retain, and a subsequent loss of engine power. In addition, the actions specified in this AD are intended to prevent the possible high disk speed uncontained liberation of disk posts and turbine blades, which could cause aircraft damage.
97-02-01: This amendment adopts a new airworthiness directive (AD) that applies to The New Piper Aircraft, Inc. (Piper) Model PA-31T2 airplanes that have a Parker Hannifin Wheel and Brake Conversion Kit 199-111 installed in accordance with Supplemental Type Certificate (STC) SA599GL. This action requires rerouting the landing gear emergency extension line. This AD results from three incidents of the brake cylinder contacting the landing gear emergency extension air line on both wheel wells. The actions specified by this AD are intended to prevent the brake cylinder from chafing against the landing gear emergency extension air line when the gear is in the up and locked position, which could result in damage to the air line and subsequent loss of emergency gear extension capability.
2021-07-17: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-900ER series airplanes. This AD was prompted by reports of significant corrosion of electrical connectors located in the main landing gear (MLG) wheel well. This AD requires repetitive records checks to determine exposure to certain deicing fluids or repetitive inspections for corrosion of the electrical connectors, and corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2021-09-02: The FAA is superseding Airworthiness Directive (AD) 2021-04-07 which applied to certain Piper Aircraft, Inc., (Piper) Models PA-46- 350P (Malibu Mirage), PA-46R-350T (Malibu Matrix), and PA-46-500TP (Malibu Meridian) airplanes. AD 2021-04-07 required identifying and correcting nonconforming stall warning heat control systems. Since AD 2021-04-07 was issued, the FAA was notified of an error in the stall warning heat control modification kit part number. This AD retains all of the actions in AD 2021-04-07 and corrects the incorrect modification kit part number. The FAA is issuing this AD to address the unsafe condition on these products.
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.