Results
2005-20-40: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200CB, and -200PF series airplanes. This AD requires an inspection of each trailing edge flap transmission assembly to determine the part number and serial number, and related investigative and corrective actions and part marking if necessary. This AD results from a report indicating that cracked flap transmission output gears have been discovered during routine overhaul of the trailing edge flap transmission assemblies. We are issuing this AD to prevent an undetected flap skew, which could result in a flap loss, damage to adjacent airplane systems, and consequent reduced controllability of the airplane.
2017-17-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by a report of fatigue cracking found in a certain fuselage frame common to the water tank support intercostal clip located between certain stringers. This AD requires inspections for any cracking of a certain fuselage frame, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-16-09: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model MYSTERE-FALCON 50 airplanes and FALCON 2000 airplanes. This AD was prompted by a report indicating that during ground maintenance, a Model FALCON 2000 airplane experienced a loss of hydraulic pressure affecting both hydraulic systems due to damage to both brake hoses on the main landing gear (MLG). This AD requires an inspection for certain brake hoses, installation of protective wraps or installation of certain brake hoses, and replacement of certain brake hoses. We are issuing this AD to address the unsafe condition on these products.
2005-20-27: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A340-211, -212, -311, and -312 airplanes. This AD requires an initial rotating probe inspection and initial and repetitive ultrasonic inspections for discrepancies of the first fastener hole of the horizontal flange of the keel beam on previously modified airplanes, installation of new fasteners, and corrective action if necessary. This AD results from a report that certain inspections done before accomplishing the modification of the lower keel beam fitting and forward lower shell connection, revealed cracking that was outside the modification limits specified in the service bulletin; the cracking was repaired by installing a titanium doubler. We are issuing this AD to find and fix discrepancies of the fastener holes of the horizontal flange of the keel beam, which could result in reduced structural integrity of the fuselage.
2017-17-04: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of cracks in the upper aft skin of the right wing at certain fastener holes along the rear spar upper chord. This AD requires repetitive inspections for cracking of the upper aft skin of the wings, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
80-13-13: 80-13-13 DEHAVILLAND: Amendment 39-3816. Applies to all DHC-6 model airplanes equipped with floats, certificated in all categories. To prevent spreader strut lug failure and interference between float fitting and front strut, accomplish the following: (a) On aircraft Serial Numbers 1 thru 611 incorporating S.0.0. 6002 and 6082 float and chassis installation, within 100 hours in service or one month, whichever occurs first, after the effective date of this AD, unless previously accomplished, incorporate modifications in accordance with DeHavilland Service Bulletin 6/330, Revision "C", dated February 29, 1980, or approved equivalent modification. (b) On all aircraft with front spreader struts P/N C6UF1014-1, within 200 hours in service or two months, whichever occurs first, after the effective date of this AD, unless previously accomplished, incorporate modification in accordance with DeHavilland Service Bulletin 6/357, Revision "C", dated February 29, 1980, or approved equivalent modification. (c) Equivalent modifications must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (d) Compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA Maintenance Inspector. This amendment is effective July 1, 1980.
2003-19-14 R2: The FAA is revising Airworthiness Directive (AD) 2003-19-14 R1, which applies to certain BURKHART GROB LUFT--UND RAUMFAHRT GmbH & CO KG (GROB) Models G103 TWIN ASTIR, G103A TWIN II ACRO, and G103C TWIN III ACRO sailplanes. AD 2003-19-14 R1 requires you to modify the airspeed indicators, install flight speed reduction and aerobatic maneuver restrictions placards (as applicable), and revise the flight and maintenance manuals. AD 2003-19-14 R1 approves simple aerobatic maneuvers for Model G103A TWIN II ACRO sailplanes and provides an option for modifying the rear fuselage for Models G103A TWIN II ACRO and G103C TWIN III ACRO sailplanes to terminate the flight limitation restrictions for aerobatic maneuvers. This AD retains all the actions from AD 2003-19-14 R1 for Models G103A TWIN II ACRO and G103C TWIN III ACRO and reinstates certain operating limits for Model G103 TWIN ASTIR sailplanes. We are issuing this AD to prevent damage to the fuselage during limit load flight, which could result in reduced structural integrity. This condition could lead to loss of control of the sailplane. \n\n\nDATES: This AD becomes effective on November 30, 2005. \n\n\tOn August 12, 2004 (69 FR 34258, June 21, 2004) the Director of the Federal Register approved the incorporation by reference GROB Service Bulletin No. MSB315-65, dated September 15, 2003; GROB Service Bulletin No. OSB 315-66, dated October 16, 2003; and GROB Work Instruction for OSB 315-66, dated October 16, 2003. \n\n\tAs of November 30, 2005, the Director of the Federal Register approved the incorporation by reference of GROB Service Bulletin No. MSB315-64/3, dated September 14, 2004.
82-18-07: 82-18-07 CANADAIR: Amendment 39-4446. Applies to Canadair Model CL-600-1A11 airplanes, serial numbers 1005 through 1007, 1010 through 1014, and 1016 through 1023, certificated in all categories. Compliance is required as indicated to prevent possible temporary interruption of the stall protection system stick pusher capability. Accomplish the following unless already accomplished: 1. Within the next 25 hours time in service, modify the stall protection system in accordance with instructions contained in Canadair Alert Service Bulletin A600-0090, Revision 1, dated October 28, 1981. 2. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 3. 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. The 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). This amendment becomes effective September 7, 1982.
69-16-01: 69-16-01\tBOEING: Amdt. 39-838. Applies to Boeing Model 727, 727C, and 727-200 Series Airplanes. \n\tCompliance required within 300 hours time in service after the effective date of this AD as indicated, unless already accomplished. \n\tTo provide the flight crew with more complete procedures to be followed if all generators are lost change the Airplane Flight Manual to read the following, or make an equivalent change approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\t(a)\tBoeing 727 series (except 727-31, -31C, and 231), Airplane Flight Manual, Emergency Procedures Section, Loss of All Generators paragraph, must be revised to read: \n\tLOSS OF ALL GENERATORS \n\tPhase I \n\tEssential power selector - STANDBY \n\tBattery Switch - Check ON \n\tPHASE II \n\tAny generator field relay - CLOSE \n\tRepeat if necessary until voltage and frequency of a generator are normal. \n\tWhen voltage and frequency are normal switch essential power selector to operating generator. \n\tNOTE: If a differential fault is indicated in any generator system, an automatic lockout feature prevents closing of the field relay. This lockout feature can be bypassed by momentarily moving the battery switch to OFF, then back ON, or by manually tripping and resetting the associated generator DC control circuit breaker. \n\tPhase III \n\tRestore system to normal if desired. \n\tNOTE: Leave generator supplying essential power isolated until system integrity is verified. \n\tRemove heavy electrical loads (galleys, air conditioning pack fans, etc.) or \n\tOpen bus tie breakers (if closed) before closing Generator Control Breakers. \n\tFor further information, see electrical systems operation, Normal Procedures - Section III. \n\t(b)\tBoeing 727 series 727-31, -31C, and 231, Airplane Flight Manual, Emergency Procedures Section, Loss of All Generators paragraph, must be revised to read: \n\tLOSS OF ALL GENERATORS \n\tPhase I \n\tEmergency Power Switch - ON \n\tBattery Switch - Check ON \n\tPhase IIAny generator field relay - CLOSE \n\tRepeat if necessary until voltage and frequency of a generator are normal. \n\tWhen voltage and frequency are normal switch essential power selector to operating generator. \n\tNOTE: If a differential fault is indicated in any generator system, an automatic lockout feature prevents closing of the field relay. This lockout feature can be bypassed by momentarily moving the battery switch to OFF, then back ON, or by manually tripping and resetting the associated generator DC control circuit breaker. \n\tPhase III \n\tRestore system to normal if desired. \n\tNOTE: Leave generator supplying essential power isolated until system integrity is verified. \n\tRemove heavy electrical loads (galleys, air conditioning pack fans, etc.) or \n\tOpen bus tie breakers (if closed) before closing Generator Control Breakers. \n\tFor further information, see electrical system operation, Normal Procedures - Section III. \n\tThe effective date of amendment 39-810 is revised to"August 15, 1969." \n\tEffective August 15, 1969. \n\tRevised September 12, 1969.
2017-15-14: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-215-6B11 (CL-415 Variant) airplanes. This AD was prompted by a report indicating that an oxygen bottle was found loose while the clamp strap was in the locked position. This AD requires modification of the clamp strap and installation of additional shims, as applicable, to the flight crew's oxygen bottles' retaining structures. We are issuing this AD to address the unsafe condition on these products.