Results
2016-08-12: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 787-8 and 787-9 airplanes powered by General Electric (GE) GEnx-1B engines. This AD requires revising the airplane flight manual (AFM) to provide the flight crew a revised fan ice removal procedure and a new associated mandatory flight crew briefing to reduce the likelihood of engine damage due to fan ice shedding. This AD also removes certain dispatch relief. For airplanes with certain engines, this AD also requires reworking or replacing at least one engine. This AD was prompted by a recent engine fan blade rub event that caused an in-flight non-restartable power loss. We are issuing this AD to prevent susceptibility to heavy fan blade rubs, which could result in engine damage and a possible in-flight non-restartable power loss of one or both engines.
98-04-04: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Model TBM 700 airplanes. This AD requires replacing the starter generator mounting adapter with a part of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent loss of the starter generator caused by failure of the starter generator mounting adapter, which could result in loss of electrical power.
80-17-14: 80-17-14 BENDIX: Amendment 39-3886. Applies to Bendix D-2000 and D-2200 series magnetos installed on 4, 6, or 8 cylinder reciprocating engines. To preclude the loss of ignition, accomplish the instructions shown in the following sections of Bendix Service Bulletin No. 605A or an FAA-approved equivalent, within the next 50 hours' time in service after the effective date of this AD unless previously accomplished. a. Service Bulletin Section 2, Housing Distortion Check: 1. For red nameplate magnetos with serial numbers above 25000. 2. For any magneto, regardless of serial number, which has operated with the four center cover screws installed after compliance with AD 79-18-06. b. Service Bulletin Section 4, Installation of Cover Sealing Kit and Cover Decals. c. Service Bulletin Section 5, Identification After Compliance. d. Make an engine log book entry of compliance, including magneto serial number. Equivalent inspections and procedures mustbe approved by the Chief of the Engineering and Manufacturing Branch, AEA-210, Federal Aviation Administration (FAA) Eastern Region. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this Airworthiness Directive can be accomplished. This amendment is effective August 21, 1980.
62-22-03: 62-22-03 VICKERS: Amdt. 491 Part 507 Federal Register October 5, 1962. Applies to All Viscount 700 Series Aircraft. Compliance required as indicated. As a result of wing flap attachment difficulties the following is required for both flap assemblies: (a) (1) Replace bolts P/N's 72403-2445, 70103-2645, and 70103-2639, at flap support bracket units Nos. 2 and 3 respectively, right and left side with new bolts every 1,500 landings. (2) Replace bolts P/N's 70003-2359 and 70107-467, at flap support bracket units Nos. 1 and 4 respectively, right and left side with new bolts every 2,500 landings. (3) When Modification D.2175 is incorporated and provided the bolts referred to in paragraphs (a)(1) and (a)(2) are replaced with new bolts at the same time, the life of these new bolts is extended as specified in the overhaul schedule listed below: Part Number 72403-2445 - Retirement time 4,500 landings Part Number 70103-2645 - Retirement time 4,500 landings PartNumber 70103-2639 - Retirement time 4,500 landings Part Number 70003-2359 - Retirement time 7,500 landings Part Number 70107-467 - Retirement time 7,500 landings (b) Flap beam (supporting bracket) attachment fitting at wing trailing edge false spar member inspection. (1) Within the next 135 hours' time in service after the effective date of this AD and each 135 hours' time in service thereafter, visually inspect for cracks all four lower flap support attachment fittings aft of the wing trailing edge member (false spar) on the right and left sides. The initial inspection is not required if these fittings were thoroughly examined at the time of bolt replacement of paragraph (a). (2) Within the next 385 hours' time in service after the effective date of this AD and each 1,080 hours' time in service thereafter, visually inspect for cracks all the flap support attachment fittings forward of the trailing edge member (false spar), top and bottom, right and left sides at flap positions 2 and 3. (3) Within the next 385 hours' time in service after the effective date of this AD and each 385 hours' time in service thereafter, visually inspect for cracks all top beam attachment fittings aft of the trailing edge member (false spar) on the right and left sides. (c) Replace cracked fittings. (d) Incorporated Vickers Modification D.2175 within the next 400 hours' time in service after the effective date of this AD on aircraft exceeding 3,000 landings, or within 400 hours' time in service upon the accumulation of 3,000 landings on aircraft not exceeding 3,000 landings on the effective date of this AD. Upon incorporation of this modification, the inspections called for in (b)(1), (b)(2), and (b)(3) may be discontinued. (Vickers Viscount 700 Series PTL No. 151, Issue 4 covers this subject.) This supersedes AD 57-07-03. This directive effective November 6, 1962.
2005-19-02: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-110P1 and EMB-110P2 airplanes. This AD requires repetitive inspections for corrosion or cracking of the rotating cylinder assembly in the nose landing gear (NLG), and related investigative/corrective actions if necessary. This AD also requires the eventual replacement of the rotating cylinder assembly with a new part, which terminates the need for the repetitive inspections. This AD results from reports of corrosion on the NLG rotating cylinder assembly. We are issuing this AD to prevent cracks from emanating from corrosion pits in the NLG rotating cylinder assembly, which could result in failure of the NLG.
98-03-18: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0100 and 0070 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to include information that will enable the flightcrew to identify failures of the emergency direct current (DC)/alternating current (AC) bus power supply and to take appropriate corrective actions. This amendment requires a new terminating modification for the existing AFM revisions. This amendment also requires a new AFM revision to inform the flightcrew that, under certain conditions, an "EMER DC BUS" warning on the multi-function display unit (MFDU) will occur, and to take appropriate corrective actions. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failures of the emergency DC/AC bus power supply, which could reduce theability of the flightcrew to control the airplane.
98-03-13: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA and SD3 SHERPA series airplanes, that requires removing the aluminum alloy oxygen pipe assembly and replacing it with a stainless steel assembly. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent aluminum oxygen tubing from bursting and releasing a high-pressure oxygen flow into the passenger cabin, which could result in a fire hazard during flight.
98-03-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737, 747, 757, and 767 series airplanes, that currently requires a one-time operational test of the pilots' seat locks and the seat tracks to ensure that the seats lock in position and the seat tracks are aligned correctly; and re-alignment of the seat tracks, if necessary. This amendment revises the applicability of the existing AD. The actions specified in this AD are intended to prevent uncommanded movement of the pilots' seats during acceleration and take-off of the airplane, and consequent reduced controllability of the airplane.
60-05-01: 60-05-01 FAIRCHILD: Amdt. 109 Part 507 Federal Register March 2, 1960. Applies to Models F-27, F-27A, and F-27B, Serial Numbers 1 to 65 inclusive. Compliance required by April 15, 1960. As a result of investigation of loose rivets in the rudder torque tube assembly, the following shall be accomplished: Replace all "Olympic" rivets "Huck" lockbolts, P/N BL-8-3, in rudder torque tube assembly, P/N 727413-1, where the ends, P/N 27-727414-3 and 27-727415-3, are secured to the tube, P/N 27-727424-3. (Fairchild Service Bulletin No. 27-15, revised September 8, 1959, covers this subject.)
2017-01-04: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. This AD was prompted by an analysis which determined that, for certain areas of the fuselage, the current threshold of an Airworthiness Limitations Section inspection is insufficient to detect early crack development. This AD requires one time high and low frequency eddy current inspections of the affected fuselage skin for cracks, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2016-21-07: We are superseding airworthiness directive (AD) 2015-12-04 for all Honeywell International Inc. (Honeywell) TPE331-1, -2, -2UA, -3U, - 3UW, -5, -5A, -5AB, -5B, -6, -6A, -10, -10AV, -10GP, -10GT, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -12JR, -12UA, - 12UAR, and -12UHR turboprop engines with certain Woodward fuel control unit (FCU) assemblies, installed. AD 2015-12-04 required initial and repetitive dimensional inspections of the affected fuel control drives and insertion of certain airplane operating procedures into the applicable flight manuals. This AD corrects the compliance requirements and relaxes the inspection interval. This AD was prompted by a request to change compliance time from 50 hours to 100 hours for affected fuel controls. We are [[Page 73021]] issuing this AD to prevent failure of the fuel control drive, damage to the engine, and damage to the airplane.
85-08-03: 85-08-03 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-5041. Applies to BHTI Model 47 Series helicopters and all other helicopters, certified in all categories, equipped with tail rotor blade assembly, P/N 47-642-117-1, S/N's A-8 through A-72. Compliance is required as indicated unless already accomplished. To prevent possible failure of the tail rotor blade accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD, remove from service tail rotor blade assemblies Part Number 47-642-117-1, Serial Numbers A-8 through A-72. (b) Any equivalent method of compliance with this AD must be approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. (c) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the replacement required by this AD may be accomplished. NOTE: Alert Service Bulletin, No. 47-84-11, dated 10-16-84, pertains to this AD. This amendment becomes effective on April 29, 1985.
2002-03-03: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA--Groupe AEROSPATIALE (SOCATA) Model TBM 700 airplanes. This AD requires you to install a new strainer draining system in the cabin fuselage. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent water from accumulating in the fuselage, then freezing and interfering with or causing the elevator controls to seize. This could result in loss of elevator control with consequent loss of airplane control.
2017-01-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-115, A319-132, A320-214, A320-232, A321-211, A321- 213, and A321-231 airplanes. This AD was prompted by a report of certain tie rod assemblies installed on the hinged fairing assembly of the main landing gear (MLG) with no cadmium plating on the rod end threads. This AD requires inspection and replacement of certain tie rod assemblies installed on the hinged fairing assembly of the MLG. We are issuing this AD to address the unsafe condition on these products.
2017-01-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by a report that some inboard and outboard trailing edge flap rotary actuators may have been assembled with an incorrect no-back brake rotor-stator stack sequence during manufacturing. This AD requires inspecting the trailing edge flap rotary actuator, and replacing the rotary actuator or doing related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
98-02-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections for discrepancies of the forward engine mount bulkhead of the nacelle strut, and corrective action, if necessary. That AD also provides for optional terminating action for the repetitive inspections. For certain airplanes, this amendment adds repetitive inspections for discrepancies in the forward engine mount bulkhead and in the forward lower spar web, and corrective actions, if necessary. For other airplanes, this amendment adds a one-time inspection to detect stop drilled cracks of the exterior of the forward engine mount chord, and replacement of the chord with a new chord, if necessary. This amendment also adds an additional optional terminating action for the repetitive inspections. This amendment is prompted by reports that fatigue cracking was found in an area adjacent to the inspection area specified in the existing AD. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could lead to the failure of the forward engine mount bulkhead and consequent separation of the engine from the airplane.
51-18-01: 51-18-01 CESSNA: Applies to All Model T-50 Aircraft. Compliance required at each periodic inspection. Two reports of loss of rudder control in flight as a result of fatigue failure of rudder torque tube have been received. Failures occur in the lower rib and pylon area. For complete inspection of the affected area, a section of the fabric should be opened by cutting along the leading edge upward to permit removal of a 10-inch section of the leading edge wood block then aft along the lower rib flange. This method will facilitate closing. (Replacement of removed wood leading edge section with lacing cord similar to original fastening is satisfactory.) Since the rudder torque tube is not heat-treated, cracks up to approximately 3/4 inch in length may be stop-drilled and welded. Where cracks have progressed further, it is recommended that the lower section of the torque tube be replaced by splicing between the No. 1 and No.2 ribs in accordance with Manual 18 practice.This supersedes AD 47-05-02.
75-27-02: 75-27-02 BRITISH AIRCRAFT CORPORATION: Amendment 39-2474. Applies to British Aircraft Corporation (BAC) Viscount Models 744, 745D and 810 airplanes, certificated in all categories. Compliance is required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. To prevent failure of propeller feathering, install an electrical back-up to the primary manual feathering system in accordance with the instructions contained in BAC Bulletin-For- Modification No. FG.2122, dated February 11, 1972, (for Viscount Model 810 airplanes), or BAC Bulletin-For-Modification No. D.3245, dated February 11, 1972 (for Viscount Models 744 and 745D airplanes), as appropriate, or an equivalent of either approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, FAA-American Embassy, APO New York 09667. This amendment becomes effective on January 19, 1976.
2005-18-23: The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. That AD currently requires either determining exposure to runway deicing fluids containing potassium formate, or performing repetitive inspections of certain electrical connectors in the wheel well of the main landing gear (MLG) for corrosion, and follow-on actions. This new AD adds a new inspection requirement and related corrective actions. This AD is prompted by additional reports indicating that significant corrosion of the electrical connectors in the wheel well of the MLG has also been found on airplanes that land on runways treated with deicing fluids containing potassium acetate. We are issuing this AD to prevent corrosion and subsequent moisture ingress into the electrical connectors, which could result in an electrical short and consequent incorrect functioning of critical airplane systems essential to safe flight and landing of the airplane, including fire warning systems. \n\n\nDATES: This AD becomes effective October 19, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 737-24A1148, Revision 1, dated July 10, 2003; as listed in the AD; is approved by the Director of the Federal Register as of October 19, 2005.
2016-26-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by reports indicating that certain wing side-of-body upper stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. This AD requires inspections of certain stringer fittings, replacement if necessary, and replacement of certain fasteners. We are issuing this AD to address the unsafe condition on these products.
2016-20-04: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA341G and SA342J. This AD prohibits autorotation training flights until the hardness of the landing gear rear crosstube (crosstube) is inspected. This AD is prompted by two reports of crosstubes failing during ground handling. These actions are intended to prevent failure of a crosstube, which could result in dropping or tipping of the helicopter.
83-15-09: 83-15-09 FAIRCHILD (SWEARINGEN): Amendment 39-4702. Applies to the following models and serial numbers of airplanes certificated in any category: Model SA226-T (S/N T-249 through T-275, and T-277 through T-291), Model SA226-TB (S/N T-276 and T-292 through T-417), Model SA226-AT (S/N AT-025 through AT-069, AT-071 through AT-074), Model SA226-TC (S/N TC-212 through TC-419), Any SA226 model and serial number airplane modified in accordance with Service Bulletin SB 32-016, Model SA227-AC (S/N AC-398 through AC-599) and all models with hydraulic nose wheel steering, Model SA227-AT (S/N AT-070, S/N AT-423 through AT-596), Model SA227-TT (S/N TT-421 through TT-597). Compliance: Required as indicated unless already accomplished. To assure reliable operation of the steering system: a) On or before November 1, 1983: 1) Modify the nose wheel steering systems of the affected Serial No. Model SA226-T, SA226-TB, SA226-AT, and SA226-TC airplanes in accordance with Fairchild (Swearingen) Service Bulletin SB 32-037 revised July 15, 1982, or if optional tiller wheel steering is installed, in accordance with SB 32-039 dated September 9, 1982. 2) Modify the nose wheel steering systems of the affected Serial Number Model SA227-AC, SA227-AT, and SA227-TT airplanes in accordance with Fairchild Service Bulletin SB 32-006 revised July 27, 1982. 3) When the modifications required by paragraphs a)1) and a)2) of this AD are accomplished, remove the nose wheel steering operational restrictions in the Limitations Section of the Airplane Flight Manual and placards in the airplane that were incorporated in accordance with Fairchild Swearingen Service Bulletins SBA 32-001 or SBA 32-032 both dated June 3, 1981. b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. c) An equivalent method of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, ASW-150, Federal Aviation Administration, Southwest Regional Office, P.O. Box 1689, Fort Worth, Texas 76101. This amendment becomes effective on September 8, 1983.
2005-18-21: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company Models 1900, 1900C, 1900C (C-12J), and 1900D airplanes. This AD requires you to inspect all elevator hinge support attachments on both left and right elevators for loose and missing rivets, replace rivets if loose or missing rivets are found, inspect the elevator hinge joints for looseness and clearance of each elevator to its stabilizer, correct looseness and clearance if incorrect, and report results of the required inspections. This AD results from a report of excessive movement of the elevator and elevator trim. The hinge support attachment that attaches the elevator to the horizontal stabilizer was loose and had loose and missing rivets. The elevator counterweight horn showed evidence of rubbing against the horizontal stabilizer, indicating possible incorrect clearance. We are issuing this AD to detect and correct any looseness in the elevator hinge support attachments, which could result in binding of the elevator control system. This elevator binding could lead to loss of control of the airplane.
97-25-07: This amendment supersedes an existing airworthiness directive (AD), applicable to GE Aircraft Engines (GE) CT7 series turboprop engines, that currently requires eddy current inspection (ECI) of disk holes of stage 1 and 2 gas generator turbine (GGT) disks for cracks, and, if necessary, replacement with serviceable parts. This amendment increases the initial cyclic compliance threshold while decreasing the calendar time for performing the ECI. This amendment is prompted by corrections to the applicable alert service bulletin (ASB) serial number (S/N) tables. The ASB contained S/Ns which appeared in more than one table creating confusion over which cyclic limit applied to each S/N. The actions specified by this AD are intended to prevent a stage 1 or 2 GGT disk failure, which could result in an uncontained engine failure and damage to the aircraft.
97-11-02 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that currently requires an inspection to determine the thickness of the intercostal that attaches the third crew member seat to the floor structure in the flight compartment, and replacement, if necessary. That action was prompted by a report from the manufacturer indicating that intercostals have been installed that are not of sufficient thickness (and consequent strength) to support the third crew member seat during emergency landing dynamic conditions. The actions specified by that AD are intended to prevent the failure of this intercostal during an emergency landing, which could consequently result in injury to the flight crew. This amendment revises the applicability of the existing AD by removing several airplanes.