Results
98-14-04: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100, -200, and -300 series airplanes, that requires modification of the lever assembly of the roll disconnect system. This amendment is prompted by mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent uncommanded disconnects of the roll control system, which could result in a limited degree of roll control and consequent reduced controllability of the airplane.
2017-18-21: We are superseding Airworthiness Directive (AD) 2017-13-12, which applied to all Airbus Model A318 and A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2017- 13-12 required modification or replacement of certain side stay assemblies of the main landing gear (MLG). This new AD clarifies the formatting of a figure in the published version of AD 2017-13-12. This new AD was prompted by reports indicating that affected parties misinterpreted the applicability of the affected part numbers due to the formatting of a figure in the published version of AD 2017-13-12, which could result in a negative effect on compliance. We are issuing this AD to address the unsafe condition on these products.
2017-19-07: We are superseding Airworthiness Directive (AD) 2013-02-12, which applied to all EADS CASA (now Airbus Defense and Space S.A.) Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes. AD 2013-02-12 required a one-time inspection to identify the correct polarity for each pair of electrical connectors on each engine fire extinguisher cartridge, and repair if necessary. This AD continues to require identifying the correct polarity of each pair of electrical connectors of the affected engine fire extinguisher cartridge, and doing a repair if necessary. This AD also requires modifying the installation of the fire extinguisher circuit harnesses. This AD was prompted by reports of incorrect electrical polarity connections on engine fire extinguishing discharge cartridges. We are issuing this AD to address the unsafe condition on these products.
2000-04-19: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Dassault Model Mystere-Falcon 50 series airplanes, that currently requires a revision to the Limitations section of the FAA-approved Airplane Flight Manual (AFM) to include procedures to use certain values to correctly gauge the minimum allowable N1 speed of the operative engines during operation in icing conditions. This amendment adds a new requirement for operators to adjust the thrust reverser handle stop, install new wiring, and modify the Digital Electronic Engine Control (DEEC) software, which terminates the AFM revision. 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 flightcrew use of erroneous N1 thrust setting information displayed on the Engine Indication Electronic Display (EIED), which could result in in-flight shutdown of engine(s).
2017-19-08: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model C-212-CB, C-212-CC, C-212-CD, C- 212-CE, and C-212-DF airplanes. This AD was prompted by reports of failures of the rudder pedal control system support. This AD requires modifying the rudder pedal adjustment system. We are issuing this AD to address the unsafe condition on these products.
2000-22-13: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters that requires calibration of the fuel quantity indicating system. This amendment is prompted by an operator report of an inaccurate fuel quantity indicating system. The actions specified by this AD are intended to prevent an inaccurate fuel quantity indicating system reading, engine flameout due to fuel starvation, and a subsequent forced landing.
2005-22-04: The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to determine (maintenance records check and/or inspection) whether certain nose landing gear (NLG), main landing gear (MLG), and MLG shock absorber assemblies with a serial number beginning with "AM" are installed, and, if installed, would require you to replace them with ones without the "AM." This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct the NLG, MLG, and MLG shock absorber assemblies that are affected by hydrogen embrittlement, which could result in failure of the landing gear. This failure could lead to nose or main landing gear collapse during operation with consequent loss of airplane control.
98-14-01: This amendment adopts a new airworthiness directive (AD), applicable to Model AS-350B, BA, B1, B2, and D, and Model AS-355E, F, F1, F2, and N helicopters, that requires inspections of the main gearbox suspension bi-directional cross-beam (cross-beam) for cracks, and replacement of the cross-beam if a crack is found. This amendment is prompted by several reports of cracks in the cross-beam. The actions specified by this AD are intended to provide a terminating action to prevent failure of the cross-beam that could cause the main gearbox to pivot, resulting in severe vibrations and a subsequent forced landing.
98-13-40: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA 330F, G, and J helicopters, that requires verifying the torque on the nut that secures the two transformer-rectifiers' common ground; and subsequently installing a modification to separate the grounds of the two transformer-rectifiers. This amendment is prompted by a report from the airworthiness authority of France about an unsafe condition resulting from the loss of the common ground of the two transformer-rectifiers. The actions specified by this AD are intended to prevent loss of the common ground of the two transformer-rectifiers, which could result in a complete electrical failure (essential and secondary), loss of electrically-powered instrumentation, and subsequent loss of control of the helicopter.
83-20-01: 83-20-01 GARLICK HELICOPTERS, HAWKINS & POWERS AVIATION, INC., WILCO AVIATION (BELL) MODEL UH-1B HELICOPTERS: Amendment 39-4731. Applies to Garlick Helicopters, Hawkins & Powers Aviation, Inc., and Wilco Aviation (Bell) UH-1B helicopters certified in all categories. Compliance is required within the next 100 hours time in service after the effective date of this AD unless already accomplished. To prevent excessive structural loads which could lead to mechanical failure and possible loss of a helicopter, accomplish the following: (a) Inspect the tail rotor hub assembly and identify the part number of the tail rotor hub assembly. The tail rotor hub assembly part number is located on the yoke assembly. (b) If the tail rotor hub assembly, P/N 204-011-801-003, is installed, remove and replace with P/N 204-011-801-005, 009, or 017. (c) Any equivalent method of compliance with paragraph (b) above of this AD must be approved by the Manager, Aircraft CertificationDivision, Southwest Region, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101. (d) In accordance with FAR 21.197, flight is permitted to a base where the inspections required by this AD may be accomplished. This amendment becomes effective November 1, 1983.
2005-22-03: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) (formerly Allison Engine Company) 501- D22A, 501-D22C, and 501-D22G turboprop engines. This AD requires a onetime inspection for proper metal hardness of certain 1st stage, 2nd stage, 3rd stage, and 4th stage turbine wheels. This AD results from a report of a turbine wheel found to be over dimensional limits, caused by improper metal hardness. We are issuing this AD to prevent uncontained turbine wheel failure, leading to damage of the airplane and total loss of engine power.
98-13-32: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that requires interim inspections to detect discrepancies of the main fitting subassembly of the main landing gear, and follow-on corrective actions, if necessary. This amendment also requires a one-time inspection to detect discrepancies of the fitting, repair of the fitting, if necessary, and application of new surface protection on the fitting, which would terminate the interim inspections. 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 cracking of the main fitting subassembly of the main landing gear, which could result in collapse of the main landing gear.
2005-21-06: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires repetitive inspections of the aft pressure bulkhead web for fatigue cracks, crack indications, discrepant holes, and corrosion; and repair if necessary. This AD results from reports of fatigue cracks in the aft pressure bulkhead web. We are issuing this AD to detect and correct such fatigue cracks, which could result in a rapid decompression of the airplane.
86-10-06: 86-10-06 BRITISH AEROSPACE AIRCRAFT GROUP: Amendment 39-5303. Applies to all BAe Model HS 748 airplanes, certificated in any category. Compliance is required within 60 days after the effective date of this AD. To prevent the overwing escape hatches from opening and becoming detached during flight, accomplish the following, unless already accomplished: A. Modify the overwing escape hatches in accordance with BAe Service Bulletin 52/115, dated July 4, 1984. 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. 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 inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate documentfrom the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective June 16, 1986.
63-21-03: 63-21-03 HILLER: Amdt. 631 Part 507 Federal Register October 15, 1963. Applies to Models UH-12D and UH-12E Helicopters. Compliance required as indicated. Due to fatigue cracking and brazed doubler separation of main rotor blade, Parsons P/N's 2253-1101-02 and 2253-1101-03, inspect the top and bottom surfaces of each blade after removing paint in the area adjacent to the outboard end of the steel doubler brazed to the leading edge spar (approximately 27 inches from the blade root end), for doubler separation and for cracks in the leading edge spar near the end of the doubler as follows: (a) For all main rotor blades, conduct a visual inspection of the affected areas with a 4 to 6-power magnifying glass within 10 hours' time in service from the effective date of this AD and daily thereafter. When inspecting for cracks or separation in the lower surface, the blade tip must be supported in a manner to remove all droop from the blade. (b) For all main rotor blades, conduct a dye penetrant inspection of the affected areas within the next 10 hours' time in service after October 15, 1963, and thereafter at intervals not to exceed 25 hours' time in service from the last dye penetrant inspection for blades, Serial Number 1269 and below, and at intervals not to exceed 100 hours' time in service from the last dye penetrant inspection for blades, Serial Number 1270 and above. (c) In the event of any unusual main rotor vibration that cannot be corrected by normal tracking, balancing or rigging procedures, conduct a dye penetrant inspection of the affected areas. In addition, inspect for cracks the bolt hole and adjacent milled surfaces of the main rotor blade fork P/N 52110-3 by means of a dye penetrant inspection or FAA approved equivalent. For this inspection remove nut, washer and pin. Replace cracked forks before further flight. (d) Main rotor blades with cracks or doubler separation must be removed from service before further flight. (e) The repetitive visual and dye penetrant inspections required by this AD may be discontinued after the installation of blades. Parsons P/N 2253-1101-04. (Hiller Service Information Letter No. 3037A covers this subject.) This supersedes AD 60-17-02. This directive effective October 15, 1963. Revised April 8, 1966.
98-13-36: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A, SAAB 340B, and SAAB 2000 series airplanes, that requires repetitive operational tests of the pitch trim system of the elevator trim-tab of the flight control unit to ensure that the system operates correctly, and repair if necessary. This amendment is prompted by a report of uncommanded movement of the right-hand elevator trim-tab to a maximum deflection position, which was apparently due to a failure in the aircraft harness and a fault in the pitch trim synchronizer. The actions specified by this AD are intended to prevent such uncommanded movement of the elevator trim-tab, which could lead to structural overload of the horizontal stabilizers at speeds above 180 knots, and consequent reduced controllability of the airplane.
61-03-05: 61-03-05 LUSCOMBE: Amdt. 248 Part 507 Federal Register February 7, 1961. Applies to All Model 8 Series Aircraft Incorporating Wing Fuel Tanks. Compliance required as indicated. Within 50 hours' time in service after the effective date of this directive, remove the fairing at the wing root of each wing and inspect the wing root area for interference between the forward fuel line and the aileron cable and/or aileron pulley. Remove the trim panel over the forward door post and inspect the forward door post area for interference between the forward fuel line and the aileron cable and/or pulley. If any interference is found, bend fuel line sufficiently to provide the necessary clearance. Replace any worn fuel lines being careful to provide clearance when installing the replacement fuel line. This directive effective March 9, 1961.
2017-18-13: We are superseding Airworthiness Directive (AD) 2015-22-51 for Agusta S.p.A. (Agusta) Model A109A and A109A II helicopters. AD 2015- 22-51 required pre-flight checking and inspecting each main rotor blade (blade) for a crack and replacing any cracked blade. This new AD removes the check and requires inspecting each blade more frequently. This AD is prompted by a crack that was not detected during any of the pre-flight checks. The actions of this AD are intended to address the unsafe condition on these products.
2017-16-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of failure of an aft hinge bolt assembly in the nose landing gear (NLG) aft doors. This AD requires replacement of the aft hinge bolt assembly in the left and right NLG aft doors, with new aft hinge bolt assemblies. We are issuing this AD to address the unsafe condition on these products.
2005-21-01: This amendment supersedes an existing airworthiness directive (AD) that applies to Pratt & Whitney (PW) JT8D-200 series turbofan engines. That AD currently requires installing and periodically inspecting individual or sets of certain part number (P/N) temperature indicators on the No. 4 and 5 bearing compartment scavenge oil tube and performance of any necessary corrective action. This AD requires installing and periodically inspecting two temperature indicators on all PW JT8D-200 series turbofan engines, including those incorporating high pressure turbine (HPT) containment hardware. This AD results from five uncontained HPT shaft failures. We are issuing this AD to prevent oil fires and the resulting fracture of the HPT shaft which can result in uncontained release of engine fragments; engine fire; in-flight engine shutdown; and possible airplane damage.
98-13-13: This amendment adopts a new airworthiness directive (AD), applicable to all Mitsubishi Model YS-11 and YS-11A series airplanes. This amendment requires revising the Airplane Flight Manual (AFM) to prohibit positioning the power levers below the flight idle stop. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller beta was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
2017-16-08: We are superseding Airworthiness Directive (AD) 2012-23-09, which applied to all Embraer S.A. Model ERJ 190-100 STD, -100 LR, and - 100 IGW airplanes; and Model ERJ 190-200 STD, -200 LR, and -200 IGW airplanes. AD 2012-23-09 required revising the maintenance program to incorporate certain modifications in airworthiness limitations. This new AD requires revising the maintenance or inspection program to incorporate certain modifications in the airworthiness limitations to include new inspection tasks and their respective thresholds and intervals. This AD was prompted by our determination that more restrictive maintenance requirements and airworthiness limitations are necessary. We are issuing this AD to address the unsafe condition on these products.
2005-21-04: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron (Bell) Model 47D1, 47G, 47G-2, 47G-2A, 47G-2A- 1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A and Coastal Helicopters, Inc. Model OH-13H (Tomcat Mark 5A, 6B, 6C) helicopters that have a certain scissors assembly or weld assembly scissors bracket installed. The AD requires, within 60 days, determining and recording the total hours time-in-service (TIS) for each Parts Manufacturer Approval (PMA)-produced scissors assembly and weld assembly scissors bracket and establishes a life limit for each affected part. This amendment is prompted by the need to establish a life limit on scissors assemblies and weld assembly scissors brackets produced under PMA No. PQ808SW or installed per Supplemental Type Certificate (STC) No. SH2772SW. The actions specified by this AD are intended to establish a life limit to prevent using a scissors assembly or weld assembly scissors bracket past it's life limit, which could result in failure of the part and subsequent loss of control of the helicopter.
76-08-03: 76-08-03 SCOTTISH AVIATION LTD. (Beagle Aircraft Ltd.): Amendment 39-2580. Applies to Model B-121 "PUP," Series 1, 2, and 3 airplanes, certificated in all categories. Compliance is required as indicated. To prevent a failure of the flap actuating lever and the consequent loss of airplane control, accomplish the following: (a) For airplanes with less than 400 hours total time in service on the effective date of this AD, comply with paragraph (d) of this AD within the next 25 hours time in service after the effective date of this AD or before the accumulation of 400 hours total time in service, whichever occurs later, unless already accomplished. Repeat the inspection required by paragraph (d) of this AD before the accumulation of 800 hours total time in service and, thereafter, at intervals not to exceed 100 hours time in service from the last inspection. (b) For airplanes with 400 or more hours total time in service but less than 800 hours total time in serviceon the effective date of this AD, comply with paragraph (d) of this AD within the next 25 hours time in service after the effective date of this AD, unless already accomplished. Repeat the inspection required by paragraph (d) of this AD before the accumulation of 800 hours total time in service, unless already accomplished within the previous 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection. (c) For airplanes with 800 or more total time in service on the effective date of this AD, comply with paragraph (d) of this AD within the next 25 hours time in service, after the effective date of this AD unless already accomplished within the previous 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection. (d) Comply with the following: (1) Remove wing root fillets to gain access to the flap actuating lever assemblies. (2) Remove split pins,nuts, washers and bolts that attach the flap actuating rods to the port and starboard flap actuating lever assemblies. (3) Inspect the flap actuating lever assemblies. P/N's BE.45.10181/9 (port) and BE.45.10181/15 (starboard) for cracks, using a dye-penetrant method, or an FAA-approved equivalent means. (NOTE: During the inspections conducted in accordance with paragraph (d)(3) of this AD particular attention should be directed to the actuating rod attachment boss). (4) If a cracks is found in any part of the flap actuating lever assembly as a result of any inspection required by this AD, before further flight, replace the cracked part with a new part of the same part number, or an FAA-approved equivalent, and continue to inspect the flap actuating lever assemblies in accordance with paragraph (d) of this AD at the intervals established in paragraph (a), (b) or (c) of this AD, as applicable. (5) Re-attach the flap actuating rods to the flap actuating lever assemblies using new split pins. (6) Re-rig flaps. (7) Re-install wing root fillets. (8) Perform a functional check of the flap operation. (Scottish Aviation Ltd. Mandatory Service Bulletin No. B-121/61, Issue 2 dated April 17, 1975, and Beagle "PUP" Series Service Manual No. 121/02/3.68 pertain to this subject). This amendment becomes effective April 29, 1976.
2005-20-12: The FAA is superseding an existing airworthiness directive (AD) for Type R321/4-82-F/8, R324/4-82-F/9, R333/4-82-F/12, and R334/4- 82-F/13 propeller assemblies. That AD currently requires initial and repetitive ultrasonic inspections of propeller hubs, part number (P/N) 660709201. This AD requires the same initial and repetitive ultrasonic inspections, but reduces the initial and repetitive compliance times for Type R334/4-82-F/13 propeller assemblies when used on Construcciones Aeronauticas, S.A. (CASA) 212 airplanes. This AD results from a report of a hub separation on a CASA 212 airplane. We are issuing this AD to prevent propeller hub failure due to cracks in the hub, which could result in loss of control of the airplane. DATES: Effective October 28, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of October 28, 2005. The Director of the Federal Register previously approved the incorporation by reference of certain publications as listed in the regulations as of July 27, 2004 (69 FR 34560, June 22, 2004). We must receive any comments on this AD by December 12, 2005.