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2020-08-02: The FAA is adopting a new airworthiness directive (AD) for certain Thales AVS France SAS (Thales) Global Positioning System/ Satellite Based Augmentation System (GPS/SBAS) receivers installed on airplanes and helicopters. This AD was prompted by reports that Thales GPS/SBAS receivers provided, under certain conditions, erroneous outputs on aircraft positions. This AD requires the installation of a software update to the aircraft navigation database and insertion of a change to the applicable airplane flight manual (AFM). The FAA is issuing this AD to address the unsafe condition on these products.
80-13-12 R1: 80-13-12 R1 DEHAVILLAND: Amendment 39-3815 as amended by Amendment 39-4135. Applies to all DHC-6 model airplanes, Serial Numbers 1 thru 631, equipped with intermediate or high flotation tires, skis, or floats, certificated in all categories. To prevent possible failure of the engine nacelle lower longerons due to cracking or buckling, accomplish the following: (a) For aircraft equipped with high flotation tires (37 inch diameter or larger) and operating to or from unprepared surfaces, visually inspect inner edge of each engine nacelle lower longeron daily, six to eight inches aft of forward end of longeron, for cracks or buckling. Use at least a ten power glass for crack detection. (b) For aircraft equipped with intermediate flotation tires and operating to or from unprepared surfaces, skis, or floats, visually inspect longerons in accordance with procedure and method in paragraph (a), within 24 hours in service, unless already accomplished within the last 26 hours in service. This inspection must be repeated thereafter term at intervals not to exceed 50 hours in service from the last inspection. (c) For aircraft which have been equipped with any of the above landings or flotation gear and are now equipped with standard wheels and tires, visually inspect longerons in accordance with procedure and method in paragraph (a), within 24 hours in service after the effective date of this AD, unless already accomplished. (d) If cracks or buckles are found, replace the longeron with a serviceable one of the same part number, or with an approved equivalent, before further flight. (e) All above inspections may be discontinued when Modification No. 6/1655, or approved equivalent, is accomplished. (f) Equivalent alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (g) 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. Amendment 39-3815 was effective July 1, 1980. This amendment 39-4135 is effective June 19, 1981.
91-08-51: 91-08-51 HONEYWELL: Amendment 39-7031. Docket No. 91-NM-94-AD. Applicability: Honeywell Flight Management System (FMS) one million word (1M or 700K) data bases (9104 cycle or earlier), as installed in, but not limited to, McDonnell Douglas Model MD-11 airplanes, and Boeing Model 747-400, 757, and 767 series airplanes, certificated in any category. Compliance: Required within 72 hours after the effective date of this AD, unless previously accomplished. To prevent improper navigation guidance during landing, accomplish the following: (a) Revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD into the AFM. "Do not use NDB approaches in the FMS NAV data base. Nondirectional Beacons may be used as waypoints to build a manual NDB approach." (b) Install a placard, visible to both pilots, adjacent to the Control Display Unit, stating: "Do not use NDB approaches in the FMS NAV data base." (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 (for McDonnell Douglas airplanes); or the Manager, Seattle ACO, FAA, Transport Airplane Directorate (for Boeing airplanes). NOTE: The request should be forwarded through an FAA Principal Avionics Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO or Seattle ACO, as appropriate. (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 (39-7031, AD 91-08-51) becomes effective on June 24, 1991, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T91-08-51, issued on April5, 1991, which contained this amendment.
88-18-01: 88-18-01 AIRBUS INDUSTRIE: Amendment 39-5998. Applies to Model A300 series airplanes, excluding the Model A300-600, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent the possibility that the emergency lighting will not be provided to the airplanes occupants for evacuation when the airplanes normal AC power is interrupted, accomplish the following. A. Within 10 days after the effective date of this AD, the following procedures must be applied and a copy of this AD or the changes indicated below must be inserted in the appropriate Section of the Airplane Flight Manual (AFM), as indicated below: 1. This sentence is to be inserted facing 3-02-00 page 11: "EMERGENCY PROCEDURES-DITCHING When ditching, the MIN CABIN LT selector (if installed) must be switched ON". 2. This sentence is to be inserted facing 3-02-00 page 12: "EMERGENCY PROCEDURES-EMERGENCY EVACUATION When the procedure EMERGENCY EVACUATION is applied, the EMER EXIT LT selector must be selected "ON" after parking brake is ON". 3. This sentence is to be inserted facing 4-03-00 page 1: "NORMAL PROCEDURES-TAXI Prior to push back, the MIN CABIN LT selector (if installed) must be switched "ON" and remain ON until gear retraction." 4. This sentence is to be inserted facing 4-03-00 page 4: "NORMAL PROCEDURES-LANDING Before landing, the MIN CABIN LT selector (if installed) must be switched "ON" and should remain ON until engine shutdown or until parked." 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 Operations Inspector (POI), 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 modifications required by 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5998, becomes effective September 2, 1988.
98-17-07: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0070 and Mark 0100 series airplanes, that requires inspection of the wing leading edge sections for the correct amount of bleed air exhaust holes, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent malfunction of the wing leading edge thermal anti-ice system, which could result in reduced controllability of the airplane and/or reduced structural integrity of the wing due to overheating.
2020-07-14: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747- 200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer indicating that the existing bond path design provides insufficient bond resistance margin between the fuel pump motor/impeller and structure. This AD requires replacement of the bonding jumpers on the auxiliary power unit (APU) fuel pump. This AD also requires, for certain airplanes, installation of a second bonding jumper; an inspection of the override/jettison fuel pumps and transfer/ jettison fuel pumps to determine if the bonding jumper has a one-piece braid or two-piece braid and replacement of the bonding jumper if necessary; and replacement of the bonding jumper on the electrical scavenge fuel pump. The FAA is issuing this AD to address the unsafe condition on these products.
81-10-01: 81-10-01 PIPER AIRCRAFT CORPORATION: Amendment 39-4095. Model PA-44-180 (Seminole), serial numbers 44-7995001 through 44-8095021, airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent cracks in the nose cone spars which could result in malfunction of the nose landing gear, accomplish the following: a. Within the next 50 hours time in service after the effective date of this AD, visually inspect the nose cone spars for cracks, in accordance with the instructions contained in Part I of Piper Aircraft Corporation Service Bulletin No. 695, dated September 10, 1980. If cracks are found, either modify as described in paragraph b below, or replace parts as required by Part I of the Piper Service Bulletin. The required inspection must be accomplished by a person authorized in accordance with FAR Part 43. b. Within the next 100 hours time in service after the effective date of this AD, modify the nose conespars in accordance with Piper Kit P/N 764 080V unless already accomplished. c. Make appropriate maintenance record entry. An equivalent method of compliance may be accomplished if approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. This amendment becomes effective April 30, 1981.
96-18-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that requires visual inspections to detect cracks of the fittings of the pressurized floor at frame 36, and renewal of the zone protective finish or replacement of fittings with new fittings, if necessary. This amendment is prompted by a report of fatigue cracking found on the pressurized floor fitting at frame 36 under the lower surface panel. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in failure of a floor fitting and subsequent depressurization of the fuselage.
77-17-01: 77-17-01 CANADAIR: Amendment 39-3007. Applies to all CL-44D4 and CL-44J airplanes, certificated in all categories, that have not been altered in accordance with Canadair Service Information Circular No. 151-CL44, Issue 3, dated October 26, 1976, or with an FAA- approved equivalent alteration. Compliance required as indicated. (a) To ensure the structural integrity and prevent failure of the following nose landing gear upper radius rods, accomplish the inspection in (1). Upper Radius Rod Subassembly Upper Radius Rod Item 1. 44-85045 LH Assembly Employs 44-85084 LH Rod Item 2. 44-85045-1 RH " " 44-85084-1 RH Rod Item 3. 44-85045-1000 LH " " 44-85084-2 LH Rod (1) For parts which have accumulated 1175 or more landings on the effective date of this airworthiness directive, inspect Items 1, 2, and 3 within the next 75 landings by a dye penetrant, eddy current, or ultrasonic method in accordance with the "Inspection Data" and "Inspection Procedure" sections of Canadair Service Information Circular No. 151-CL44, Issue 3, dated October 26, 1976, or with an FAA-approved equivalent inspection. (2) For parts which have not accumulated 1175 landings on the effective date of this airworthiness directive, accomplish the inspection in (a)(1) before attaining 1250 landings. (b) Repeat inspections in (a)(1) at intervals not to exceed: (1) 60 landings for non-reworked parts Item 1 and 3 (2) 200 landings for non-reworked part Item 2 (3) 30 landings for reworked parts Item 1, 2, and 3 (c) Replace cracked parts with new parts of the same part number or with approved equivalent parts, or rework cracked parts to the limitations specified in "Rework Instruction" in Canadair Service Information Circular No. 151-CL44, Issue 3, dated October 26, 1976, or with an approved equivalent procedure. (d) Replace parts reworked to the maximum limits, specified in "Rework Instruction" in theabove Service Information Circular, that have attained an additional 3000 landings from the time of such rework, or when cracks are again detected, whichever occurs first, with new parts of the same part number or with approved equivalent parts. (e) Equivalent inspections/procedures and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (f) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection times specified in this AD. This amendment is effective August 18, 1977.
2020-07-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report that during ALTS CAP or (V) ALTS CAP mode, the flight guidance/autopilot does not account for engine failure while capturing an altitude. This AD requires revising the existing airplane flight manual (AFM) to provide the flightcrew with new warnings for ''Autoflight'' and ''Engine Failure in Climb During ALTS CAP.'' The FAA is issuing this AD to address the unsafe condition on these products.