Results
99-04-09: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Limited (R-R) Dart series turboprop engines. This action requires initial and repetitive fuel burner fuel flow calibration checks, and overhaul or replacement of fuel burners. This amendment is prompted by reports of an uncontained engine failure and fire due to HPT disk rupture caused by fuel burner failure. The actions specified in this AD are intended to prevent HPT disk rupture, which can result in an uncontained engine failure, engine fire, and damage to the aircraft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of February 25, 1999. Comments for inclusion in the Rules Docket must be received on or before April 12, 1999.
83-09-03: 83-09-03 BELL HELICOPTER TEXTRON, INC.: Amendment 39-4646. Applies to Bell Model 222 helicopters, S/N 47006 through 47089, certificated in all categories (Airworthiness Docket No. 83-ASW-2). Compliance is required as indicated. To prevent fatigue failure of the main rotor trunnion, P/N 222-010-154-101, and mast assembly, torquemeter, P/N 222-040-002-103, which could result in loss of a helicopter, accomplish the following: (a) For main rotor trunnions, P/N 222-010-154-101, with 2400 or more hours time in service on the effective date of this AD, retire the main rotor trunnion within the next 100 hours time in service. (b) For mast assemblies, torquemeter, P/N 222-040-002-103, with 3500 or more hours time in service on the effective date of this AD, retire the mast assembly, torquemeter within the next 100 hours time in service if it is utilized exclusively with trunnion, P/N 222-010- 154-101. (c) For main rotor trunnions, P/N 222-010-154-101, with lessthan 2400 hours time in service on the effective date of this AD, retire the main rotor trunnion at 2500 hours. (d) For mast assemblies, torquemeter, P/N 222-040-002-103, with less than 3500 hours time in service on the effective date of this AD, retire the mast assembly, torquemeter at 3600 hours if it is utilized exclusively with trunnion, P/N 222-010-154-101. (e) For mast assemblies, torquemeter, P/N 222-040-002-103, which are used with both trunnions, P/N 222-010-154-101 and P/N 222-010-154-111, determine the retirement life by dividing the time the main rotor mast has been in service with trunnion, P/N 222-010-154- 101, by 0.72 and adding the result to the time in service with trunnion, P/N 222-010-154-111. When this total time exceeds 5000 hours, retire the mast assembly, torquemeter. (f) Any equivalent method of compliance with this AD must be approved by the Manager, Aircraft Certification Division, Southwest Region, Federal Aviation Administration. (g)In accordance with FAR 21.197, flight is permitted to a base where the requirements of this AD may be accomplished. (Bell Helicopter Alert Service Bulletin No. 222-82-17 pertains to this subject.) This amendment becomes effective May 23, 1983.
2005-26-18: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce Deutschland (formerly Rolls-Royce plc) (RRD) models Tay 650-15 and 651-54 turbofan engines. That AD currently requires borescope inspection of the high pressure compressor (HPC) stage 12 disc assembly to detect damage caused by HPC outlet guide vane (OGV) retaining bolt failure, and replacement of unserviceable parts with serviceable parts. That AD also requires as terminating action, the incorporation of a new design retention arrangement for the HPC OGV to prevent HPC OGV retaining bolt failure. This ad requires the same actions but extends the terminating action compliance time for Tay 650- 15 engines. This AD also includes references to later revisions of two of the applicable RRD service bulletins (SBs). This AD results from RRD relaxing the terminating action compliance time for Tay 650-15 engines due to reassessment by RRD. We are issuing this AD to prevent an uncontained failure of the HPCstage 11/12 disc spacer, which could result in damage to the airplane. DATES: This AD becomes effective February 3, 2006. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of February 15, 2002 (67 FR 4652, January 31, 2002).
2019-15-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A321-251N, A321-252N, A321-253N, A321-271N, A321-272N, A321-251NX, A321-252NX, A321-253NX, A321-271NX, and A321-272NX airplanes. This AD was prompted by analysis of the behavior of the elevator aileron computer (ELAC) L102 that revealed that excessive pitch attitude can occur in certain conditions and during specific maneuvers. This AD requires revising the airplane flight manual (AFM) to incorporate updated procedures and operational limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
99-03-03: This amendment supersedes an existing airworthiness directive (AD), applicable to Allison Engine Company Model AE 3007A turbofan engines, that currently requires reprogramming the Full Authority Digital Engine Control (FADEC) to software version VI.2. This amendment requires reprogramming the FADEC to a serviceable software version and reidentifying the FADEC assembly. This amendment is prompted by reports of at least seven uncommanded engine shutdowns, four of which occurred in flight, as a result of deficiencies in software version VI.2 on the AE 3007A engines and version VI.4 on the AE 3007A1/1 engines. The actions specified by this AD are intended to prevent an unintentional or uncommanded in-flight engine shutdown.
78-16-01: 78-16-01 BELL HELICOPTER TEXTRON (BHT): Amendment 39-3271. Applies to Models 206A and 206B helicopters, serial numbers 148 and 414 through 913, certificated in all categories. Compliance is required within the next 500 hours times in service after the effective date of this airworthiness directive unless already accomplished. To minimize the possibility of loss of directional control due to failure of the tail rotor drive shaft, remove and replace the tail rotor drive shaft bearing hangers with improved bearing hangers as specified below: a. REMOVE INSTALL (Shim Type) (Spring Type) One (1) hanger P/N 206-040-345-5 One (1) hanger P/N 206-040-345-9 or P/N 206-040-355-1 One (1) hanger P/N 206-040-346-5 One (1) hanger P/N 206-040-346-17 Five (5) hangers P/N 206-040-338-1 Five (5) hangers P/N 206-040-338-9 b. Shim type hangers modified to the spring type using instructions provided in Technical Bulletin No. 206-77-7 will be acceptable for compliance with this AD. c. All spring clamp type bearing hangers, P/N's 206-040-338-9, 206-040-355-1, 206-040-345-9, and 206-040-346-17 must be installed with the spring on the left side of the tail boom. d. To prevent bearing hangers from chafing the drive shaft cover, the cover must be modified in accordance with Bell Helicopter Company Technical Bulletin No. 206-76-2 dated January 7, 1976, (misdated 206-76-2), or later FAA approved revision or FAA approved equivalent. e. Removal and replacement, as prescribed by paragraph a., must be in accordance with the applicable maintenance and overhaul instructions. Bell Helicopter Company Service Bulletin No. 206-77-9 pertains to and provides instructions for accomplishing the intent of this AD. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part thereof pursuant to U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Service Manager, Bell Helicopter Textron, Post Office Box 482, Fort Worth, Texas 76101. These documents may also be examined at Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106, and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. Equivalent means of compliance with the modifications prescribed by this Airworthiness Directive may be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Post Office Box 1689, Fort Worth, Texas 76101. This amendment becomes effective September 14, 1978.
60-03-02: 60-03-02 CURTISS-WRIGHT: Amdt. 99 Part 507 Federal Register February 2, 1960. Applies to all C-46 Series aircraft including the C-46R and C-46/CW20-T aircraft. To eliminate the possibility of a fire in the cargo and baggage compartments being caused by unshielded sources of heat, compliance with CAR 4b.382(d)(See Note 1) must be accomplished by March 1, 1960. NOTE 1: Section 4b.382(d) of the Civil Air Regulations provides as follows: "Sources of heat within the compartment shall be shielded and insulated to prevent igniting the cargo." In a note to that section it further provides that "Sources of heat likely to ignite cargo include light bulbs, combustion heaters, heater ducts, electrical appliances, etc."
2005-26-16: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Airbus Model A300-600 and A310 series airplanes. That AD currently requires repetitive visual inspections to detect corrosion on the lower rim area of the fuselage rear pressure bulkhead; and follow-on actions, if necessary. This new AD requires new repetitive inspections for corrosion on the rear pressure bulkhead between stringer (STGR) 27 (right hand) and STGR27 (left hand), and related investigative and corrective actions if necessary. This AD also requires sending a report of certain information to the manufacturer. The AD also adds airplanes to the applicability of the existing AD. This AD results from findings of severe corrosion on airplanes previously inspected in accordance with the existing AD. We are issuing this AD to detect and correct corrosion at the lower rim area of the fuselage rear pressure bulkhead, which could result in reduced structural integrity of the bulkhead, andconsequent decompression of the cabin.
2019-15-08: The FAA is superseding Airworthiness Directive (AD) 2002-07- 05, which applied to all Airbus Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R series airplanes, and Model A300 F4-605R airplanes. AD 2002-07-05 required repetitive inspections for cracking of certain fittings, corrective action if necessary, and, for certain airplanes, a modification. This AD requires repetitive inspections for cracking of certain fittings, corrective actions if necessary, and, for certain airplanes, a modification; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that, for certain airplanes, the existing inspection compliance times were not sufficient to address the unsafe condition and needed to be reduced. The FAA is issuing this AD to address the unsafe condition on these products.
99-03-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Schempp-Hirth K.G. (Schempp-Hirth) Models Standard-Cirrus, Nimbus-2, JANUS, and Mini-Nimbus HS-7 sailplanes. This AD requires installing a safety device for the tailplane locking hook. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the locking hook on the tailplane attachment bracket from disengaging, which could result in the horizontal tailplane coming loose from the fin with possible loss of longitudinal control of the sailplane.
2005-26-12: The FAA adopts a new airworthiness directive (AD) to supersede AD 2004-08-13, which applies to certain BURKHARDT GROB LUFT-UND RAUMFAHRT GmbH & CO KG (Burkhardt Grob) Models G103 TWIN ASTIR, G103 TWIN II, G103 TWIN III ACRO, and G103 C Twin III SL sailplanes. AD 2004-08-13 currently requires you to replace the center of gravity (CG) release hook attachment brackets with brackets of improved design. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. This AD retains all the actions required in AD 2004-08-13 and adds Model G103A TWIN II ACRO sailplanes to the applicability. We are issuing this AD to prevent abnormal or uncontrolled sailplane release due to cracked CG release hook attachment brackets. This condition could result in reduced or loss of sailplane control. DATES: This AD becomes effective on February 6, 2006. On June 4, 2004 (69 FR 21402, April 21, 2004), the Director of the Federal Register approved the incorporation by reference of Grob Service Bulletin No. MSB315-62, dated January 21, 2002, and Grob Service Bulletin No. MSB869-22, dated January 22, 2002. As of February 6, 2006, the Director of the Federal Register approved the incorporation by reference of Grob Service Bulletin No. MSB315-62/2, dated March 9, 2005.
2000-22-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes, that currently requires repetitive radiographic and ultrasonic or eddy current inspections, and modification of the upper cap of the front spar of the left and right engine pylons, if necessary. This amendment requires new, improved x-ray and eddy current inspections to detect cracks of the upper cap of the front spar of the left and right engine pylons, and repetitive inspections or corrective actions, if necessary. This amendment also requires modification of the subject area, which constitutes terminating action for the repetitive inspection requirements. This amendment is prompted by additional reports of fatigue cracking in the subject area of these airplanes. The actions specified by this AD are intended to prevent failure of the upper cap of the front spar of the engine pylons due to fatigue cracking, and consequent reduced structural integrity of the airplane.
70-18-06: 70-18-06\tBOEING: Amdt. 39-1077. Applies to Model 737 series airplanes listed in Boeing Alert Service Bulletin 52-1034, dated July 24, 1970, or later FAA approved revision. \n\n\tCompliance required within the next 400 hours time in service after the effective date of this AD unless already accomplished. \n\n\tTo prevent the separation of the overwing emergency hatch handle cover from the hatch handle assembly causing confusion and possible blockage during an emergency egress, rework the hatch handle cover in accordance with Boeing Service Bulletin 52-1034, dated July 24, 1970, or later FAA approved revision, or an equivalent rework procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective September 10, 1970.
2019-15-09: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-400 series airplanes. This AD was prompted by a report of a cracked outboard spoiler actuator mounting bracket. This AD requires repetitive inspections of the outboard spoiler actuator mounting brackets, replacement of any cracked bracket, and eventual replacement of all brackets with a re-designed part that would terminate the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
76-06-03: 76-06-03 SCHEIBE FLUGZEUGBAU GmbH: Amendment 39-2552. Applies to SF 26A gliders, certificated in all categories. Compliance is required as indicated. To prevent the possible loss of lateral control, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours time in service from the last inspection, visually inspect the aileron bellcranks near the weld of the middle bearing bushing for cracks with a magnifying glass of at least 5 power, in accordance with Scheibe Technical Note No. 232-1/75 dated October 7, 1975, 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 the cracked aileron bellcrank, in accordance with FAR 43.13. This amendment becomes effective March 29, 1976.
72-22-04: 72-22-04 BEECH: Amendment 39-1546. Applies to Beech Models 60 series (Serial Numbers P-1 thru P-200 and P-210) airplanes which have a moisture barrier at fuselage station 306.421. Compliance: Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible interference with elevator movement, accomplish the following: A) Starting at the cut out for the elevator bell crank, slit the moisture barrier vertically upward utilizing a knife, razor blade or other similar tool. Extend this cut through the Velcro strip which attaches the moisture barrier to the front spar of the horizontal stabilizer. NOTE: In making the slit do not damage the spar. B) Any equivalent method of compliance with this AD must be submitted and approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective October 31, 1972.
2019-14-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-251N and -271N airplanes; and Model A321- 251N, -253N, -271N, and -272N airplanes. This AD was prompted by a report that during a calibration check, some torqueing tools used on the final assembly line have been found out of tolerance. This AD requires retorqueing each affected connection of sense and fire extinguishing lines within the pylon area to a correct torque value, as specified in an European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-26-09: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-7R4 turbofan engines. This AD requires inspection of the blade root thickness of 1st stage fan blades identified by part number (P/N) and serial number (SN) in this AD, by a repair station approved by PW to perform the inspection. This AD results from a report that a repair station created their own repair and performed it on 520 1st stage fan blades, without approval from PW. We are issuing this AD to prevent 1st stage fan blade fracture and uncontained engine failure, resulting in possible damage to the airplane.
2001-24-27: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; Model DC-9-81, -82, -83, and -87 series airplanes; Model MD-88 airplanes; and C-9 airplanes, that currently requires repetitive inspections to detect cracking of the rudder pedal adjuster hub assembly, and replacement of the assembly, if necessary. That AD also provides for an optional terminating action for the repetitive inspections. This amendment requires accomplishment of a new terminating action for the repetitive inspections. This amendment is prompted by that FAA's determination that further rulemaking is necessary. The actions specified by this AD are intended to \nprevent loss of rudder pedal control and reduction of braking capability.
78-14-04: 78-14-04 BURKHART GROB: Amendment 39-3254. Applies to Model "G102" Astir CS gliders, serial numbers 1180 through 1536, certificated in all categories, that have rudder control levers with lightening cutouts. Compliance is required with in the next 25 hours time in service after the effective date of this AD, unless already accomplished. To reduce the possibility of failure of the intermediate rudder control lever and subsequent loss of rudder control, replace the rudder control lever in accordance with Burkhart Grob, Technical Information TM 102-8, dated November 28, 1977, or equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region. This amendment becomes effective July 11, 1978.
82-06-06: 82-06-06 CANADAIR: Amendment 39-4346. Applies to Model CL-600 airplanes serial numbers 1012 thru 1024 certificated in all categories. To prevent damage to the flap drive shafts, accomplish the following: 1. Within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the last 100 hours time in service, and thereafter at intervals not to exceed 150 hours time in service, inspect the left and right flap drive shafts for damage between WS220 and WS264, in accordance with paragraphs 2.A and 2.B of Canadair Alert Service Bulletin No. A600-0037, Revision 1, dated October 28, 1981. If either drive shaft is damaged beyond the service bulletin limits, replace the shaft prior to further flight. 2. Before the accumulation of 550 hours time in service or within the next 50 hours time in service, whichever occurs later, unless already accomplished, install clamp supports for the left and right flap drive shafts at WS237.10, in accordance with paragraph 2.D of the Canadair Alert Service Bulletin. 3. The inspections required by paragraph (1) are terminated by incorporation of the clamp support in accordance with paragraph (2) of this AD. 4. Airplanes may be flown in accordance with FAR 21.197 to a maintenance base for accomplishment of the inspection required by this AD. 5. Alternate methods of compliance with this AD may be used when they provide an equivalent level of safety and are approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 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 March 22, 1982.
2005-26-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 series airplanes; and Model A320-111 airplanes. This AD requires revising the airplane flight manual by incorporating new procedures to follow in the event of a fuel leak. This AD results from a determination that, once a fuel leak is detected, fuel management procedures are a critical factor in limiting the consequences of the leak. We are issuing this AD to ensure that the flightcrew is advised of appropriate procedures to follow in the event of a fuel leak, such as isolating the fuel tanks, stopping any fuel transfers, and landing as soon as possible. Failure to follow these procedures could result in excessive fuel loss that could cause the engines to shut down during flight.
2019-14-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 Freighter series airplanes. This AD was prompted by reports of cracked flexible hoses of the oxygen crew and courier distribution system (OCCDS) on A330 freighter airplanes. This AD requires repetitive detailed inspections, including functional testing, of the OCCDS and replacement of affected part(s) if necessary, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
98-26-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes that have been converted from a passenger to a cargo-carrying ("freighter") configuration, that requires limiting the payload on the main cargo deck by revising the Limitations Sections of all Airplane Flight Manuals (AFM), AFM Supplements, and Airplane Weight and Balance Supplements for these airplanes. This amendment also provides for the submission of data and analyses that substantiate the strength of the main cargo deck, or modification of the main cargo deck, as optional terminating action for these payload restrictions. This amendment is prompted by the FAA's determination that under certain conditions unreinforced floor structure of the main cargo deck is not strong enough to enable the airplane to safely carry the maximum payload that is currently allowed in this area. The actions specified by this AD are intended to prevent failure of the floor structure, which could lead to loss of the airplane.
2019-14-05: The FAA is adopting a new airworthiness directive (AD) for certain B/E Aerospace Fischer GmbH (B/E Aerospace Fischer) Common Seats 170/260 H160. This AD was prompted by the discovery during testing that the energy absorber (EA) may not function as intended during emergency landing. This AD requires removing and replacing the EA assemblies on the affected seats. The FAA is issuing this AD to address the unsafe condition on these products.