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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.