Results
2022-17-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 airplanes. This AD was prompted by a report indicating that the inflatable free aisle restrictor (IFAR) on certain single lane slide-rafts demonstrated inconsistent release behavior in aft wind conditions. This AD requires replacing an affected part with a serviceable part, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
96-22-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200, -300, and -400 series airplanes, that requires modification of the left and right inboard elevator servo assemblies and the hydraulic routing of the right inboard elevator power control package (PCP). This amendment is prompted by a report of an uncommanded right elevator deflection after takeoff and reports of elevator/control column bumps during landing gear retraction on these airplanes. The actions specified by this AD are intended to prevent uncommanded elevator deflection, which could result in structural damage and reduced controllability of the airplane.
78-01-11: 78-01-11 MCDONNELL DOUGLAS: Amendment 39-3116. Applies to all passenger and passenger/cargo Model DC-9 airplanes certificated in all categories, including C-9A, C-9B and VC-9C. \n\n\tCompliance required within 180 days from the effective date of this AD, unless already accomplished. \n\n\tTo identify the location and operation of the tail cone emergency exit release handle, accomplish the following: \n\n\tModify the tail cone emergency exit release handle locating and operating markings in accordance with McDonnell Douglas Service Bulletin 53-134, Revision 1, dated December 16, 1977 or later FAA approved revision, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis Amendment becomes effective February 13, 1978.
2004-20-01: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) models PW123, PW123B, PW123C, PW123D, PW123E, PW123AF, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, and PW127G turboprop engines. This AD requires initial and repetitive gap inspections of the bypass valve cover, on certain part number (P/N) mechanical fuel controls (MFCs), and replacement of those MFCs as mandatory terminating action to the repetitive inspections. This AD is prompted by sixteen reports of loss of engine throttle response and overspeed, eight of which resulted in in-flight shutdown. We are issuing this AD to prevent loss of throttle response and overspeed, resulting in engine in-flight shutdown.
90-21-13: 90-21-13 BOEING: Amendment 39-6751. Docket No. 90-NM-67-AD. \n\n\tApplicability: Model 747 series airplanes, line position 001 through 331, identified in Boeing Service Bulletin 747-29-2051, Revision 1, dated August 8, 1980, certificated in any category.\n \n\tCompliance: Required within the next 4,000 flight hours or 12 months after the effective date of this AD, whichever occurs first, unless previously accomplished. \n\n\tTo prevent damage to hydraulic and pneumatic systems and flight deck/cabin air contamination, accomplish the following: \n\n\tA.\tModify the hydraulic system in the number 2 and 3 struts in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-29-2051, Revision 1, dated August 8, 1980.\n \n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.\n \n\tNOTE: The request should be forwarded through an FAA Principal Inspector (PI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to The Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6751, AD 90-21-13) becomes effective on November 12, 1990.
91-22-05: 91-22-05 BOEING: Amendment 39-8065. Docket No. 91-NM-55-AD. \n\n\tApplicability: Model 747 series airplanes, line numbers 001 through 708, except Model 747-400 and freighters, certificated in any category. \n\n\tCompliance: Required within 36 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent injury to passengers and flight attendants, accomplish the following: \n\n\t(a)\tFor airplanes listed in Boeing Service Bulletin 747-25-2734, Revision 1, dated May 25, 1989:\n\n\t\t(1)\tFor those stowage bins used for stowage, accomplish the following in accordance with Section III of Boeing Service Bulletin 747-25-2734, dated November 3, 1988, or Revision 1, dated May 25, 1989: \n\n\t\t\t(i)\tReplace the overhead stowage compartment doors and counterbalance assemblies; \n\n\t\t\t(ii)\tRework and adjust compartments; \n\n\t\t\t(iii)\tInstall new wiring provisions; and \n\n\t\t\t(iv)\tPerform operational checks of associated equipment. \n\n\t\t(2)\tFor those bins that are notused for stowage of any item, in lieu of the procedures required by paragraph (a)(1) of this AD, operators may accomplish the following: \n\n\t\t\t(i)\tConduct a visual inspection of the existing latches for wear of the latching handle locking grooves and ensure full travel of the latch pins. If wear or other discrepancies are indicated, repair in accordance with FAA-approved procedures. \n\n\t\t\t(ii)\tInstall a placard indicating "NO STOWAGE;" and \n\n\t\t\t(iii)\tDisable the bin to prevent its opening, in a manner approved by the FAA Principal Maintenance Inspector. \n\n\t(b)\tFor airplanes not listed in Boeing Service Bulletin 747-25-2734, Revision 1, dated May 25, 1989: \n\n\t\t(1)\tFor those stowage bins used for stowage, accomplish the following in a manner similar to that described in the service bulletin and approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate: \n\n\t\t\t(i)\tReplace the overhead stowage compartment doors and counterbalance assemblies; \n\n\t\t\t(ii)\tRework and adjust compartments; \n\n\t\t\t(iii)\tInstall new wiring provisions; and \n\n\t\t\t(iv)\tPerform operational checks of associated equipment. \n\n\t\t(2)\tFor those bins that are not used for stowage of any item, in lieu of the procedures required by paragraph (b)(1) of this AD, operators may accomplish the following: \n\n\t\t\t(i)\tConduct a visual inspection of the existing latches for wear of the latching handle locking grooves and ensure full travel of the latch pins. If wear or other discrepancies are indicated, repair, in accordance with FAA-approved procedures. \n\n\t\t\t(ii)\tInstall a placard indicating "NO STOWAGE;" and \n\n\t\t\t(iii)\tDisable the bin to prevent its opening, in a manner approved by the FAA Principal Maintenance Inspector. \n\n\t(c)\tAn 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, Seattle ACO, FAA, Transport Airplane Directorate. \n\n\tNOTE:The request should be forwarded through an FAA Principal Maintenance Inspector (PMI) who may concur or comment and then sent it to the Manager, Seattle ACO. \n\n\t(d)\tSpecial 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. \n\n\t(e)\tThe requirements for replacement, rework and adjustment, inspections, and operational checks shall be done in accordance with Boeing Service Bulletin 747-25-2734, dated November 3, 1988; or in accordance with Boeing Service Bulletin 747-25-2734, Revision 1, dated May 25, 1989, which includes the following list of effective pages: \n\n\n\nPAGE NUMBER\t\t\nREVISION LEVEL\n\nDATE\n 1-2, 4, 7, 9-13, 17-27, 76-77 \n\n1\nMay 25, 1989\n3, 5-6, 8, 14-16, 28-75, 78-83 \n(Original)\nNovember 3, 1988\n\nThis incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. \n\n\tThis amendment (39-8065, AD 91-22-05) becomes effective on November 29, 1991.
73-13-11: 73-13-11 MITCHELL INDUSTRIES, INC., doing business as EDO-AIRE MITCHELL: Amendment 39-1677. Applies to Mitchell automatic pilot instruments installed in various Beech aircraft with a mechanical wing flap control system in accordance with the following Supplemental Type Certificates: STC NO. BEECH AIRPLANE MODELS AUTOPILOT MODEL SA1346SW 23, A23, A23A, A23-19, 19A, A24, Century I A24R, B19, M19A, A23-24, B23,C23 Model AK341 SA1348SW 23, A23, A23A, A23-19, 19A, B19, Century IIB M19A, A23-24, B23, C23, A24, A24R Model AK342 Compliance required within the next ten (10) hours' time in service after the effective date of this AD, unless already accomplished. To prevent interference of the flap control system with the automatic pilot roll servo, which may result in loss of aileron control, accomplish the following: Remove the automatic pilot roll servo assembly and all servo installation brackets from the airplanes or install the cable tensioner Kit PKMB-8 in accordance with Edo-Aire Mitchell Service Bulletin No. MB-8 dated June 7, 1973, or later FAA approved revision, or any other method approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. The bulletin mentioned herein may be obtained from Edo-Aire Mitchell, P. O. Box 610, Mineral Wells, Texas 76067. This amendment becomes effective June 29, 1973.
96-19-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires inspection and adjustment of the torque value of the attaching parts of the interlock mechanism of the large cargo doors, removal of a spring from that mechanism, and installation of a new microswitch bracket. This amendment is prompted by a report indicating that a spring on the interlock lever of the large cargo doors may become disconnected or the lever may become jammed in the "activated" state. The actions specified by this AD are intended to prevent the spring from becoming disconnected or the lever from jamming. If other failures occur, the flightcrew could dispatch the airplane with improperly locked cargo doors; this condition could result in the opening and/or separation of the cargo doors while the airplane is in flight and subsequent rapid decompression and/or structural damage to the airplane.
2004-20-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330 and A340 series airplanes. This AD requires revising the airplane flight manual to provide procedures for the flightcrew to follow in the event of the loss of all liquid crystal display (LCD) units on airplanes equipped with the EIS2 standard of electronic instrument system. This AD is prompted by reports of the brief but total loss of all LCD units during cruise on airplanes equipped with the EIS2 standard of electronic instrument system. We are issuing this AD to provide procedures to the flightcrew to restore operation of these LCD units and prevent prolonged loss of critical flight information to the flightcrew and the consequent reduced ability of the flightcrew to control the airplane during adverse flight conditions.
90-08-01: 90-08-01 AEROSPATIALE: Amendment 39-6567. Docket No. 90-NM-40-AD. Applicability: Model ATR42-300 and ATR42-320 series airplanes, on which Modification 1236 has been installed (or which have been retrofitted in accordance with Aerospatiale Service Bulletin ATR42-52-0019), and Modification 2440 has not been installed. Compliance: Required as indicated, unless previously accomplished. To prevent simultaneous rupture of the passenger/crew door lifting device compensation rod and its fail-safe cable, accomplish the following: A. Within l5 days after the effective date of this AD, and thereafter at intervals not to exceed 250 hours time-in-service, inspect the upper part of the rod to ensure that the area is free from dents, scratches, or other damage, and inspect the fail-safe cable for damage, in accordance with Part A of Aerospatiale Service Bulletin ATR42-52-0042, Revision 1, dated January 31, 1990. 1. If damage to the rod is 0.2mm deep or more, prior tofurther flight, replace the rod with a serviceable part in accordance with the service bulletin. 2. If damage to the rod is less than 0.2mm deep, perform local blend out and apply protection (alodine, primer, and finish paint), in accordance with the service bulletin. 3. If a wire of the fail-safe cable is damaged, prior to further flight, replace the cable with a serviceable cable. B. Within 15 days after the effective date of this AD, modify the rod installation and install heat shrink tubing at the upper end of the fail-safe cable, in accordance with Part B of Aerospatiale Service Bulletin ATR42-52-0042, Revision 1, dated January 31, 1990. C. 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 Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. 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. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6567, AD 90-08-01) becomes effective on April 20, 1990.
2022-18-17: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a report of a manufacturing error that can create dents on the lower wing plank, close to the flap arm locations at certain wing stations; as a result, cracks could develop and weaken the structural integrity of the wings before being detected by any existing required inspections. This AD requires an inspection for damage (including dents, cracks, discoloration, gouges, scratches, or other surface damage) of the lower wing plank in the flap arm areas at certain wing stations, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2004-19-04: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-22B, RB211-524, and RB211-535 series turbofan engines. This AD requires revising the Time Limits Manual for RR RB211-22B, RB211-524, and RB211-535 series turbofan engines. These revisions include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD results from the need to require enhanced inspection of selected critical life-limited parts of RB211-22B, RB211-524, and RB211-535 series turbofan engines. We are issuing this AD to prevent failure of critical life-limited rotating engine parts, which could result in an uncontained engine failure and damage to the airplane.
96-13-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 series airplanes, that requires replacement of junction fittings of the horizontal stabilizer with improved fittings. For certain airplanes, this amendment also requires replacement of the drive-fitting bushings and bolts of the horizontal stabilizer with improved bushings and bolts. This amendment is prompted by reports of stress corrosion cracking in a junction fitting lug of the horizontal stabilizer. The actions specified by this AD are intended to prevent such cracking, which could result in failure of a lug and uncommanded movement of the horizontal stabilizer. This condition, if not corrected, could result in reduced controllability of the airplane.
91-07-04: 91-07-04 BOEING: Amendment 39-6933. Docket No. 90-NM-116-AD. \n\n\tApplicability: Model 737 series airplanes, line numbers 001 through 519, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent rapid decompression of the airplane, accomplish the following: \n\n\tA.\tWithin the next 3,000 cycles after the effective date of this AD, unless previously accomplished within the last 3,000 cycles, and thereafter at intervals not to exceed 6,000 cycles, perform an ultrasonic inspection for delamination of the window belt skin doubler from the fuselage skin, in accordance with Boeing Service Bulletin 737-53-1078, Revision 1, dated September 25, 1986, or Revision 2, dated April 19, 1990. \n\n\tB.\tIf delamination is found as a result of the inspections required by paragraph A. of this AD, prior to further flight, conduct a high frequency eddy current (HFEC) inspection for cracks of the skin around the countersunk fasteners in thearea of delamination and common to the window forging, in accordance with Boeing Model 737 Non-destructive Test (NDT) Manual Document D6-37239, Part 6, Subject 53-30-05, and repeat thereafter at intervals not to exceed 6,000 cycles. \n\n\tC.\tIf cracks are detected as a result of the inspection required by paragraph B. of this AD, prior to further flight, repair cracking and delamination in accordance with Boeing Service Bulletin 737-53-1078, Revision 1, dated September 25, 1986, or Revision 2, dated April 19, 1990. Further HFEC inspections for cracks under the repairs are not required. \n\n\tD.\tIf delamination is found as a result of the inspection required by paragraph A. of this AD, perform the terminating modification in accordance with Boeing Service Bulletin 737- 53-1078, Revision 1, dated September 25, 1986, or Revision 2, dated April 19, 1990, prior to the accumulation of 40,000 cycles or within the next 24 months, whichever occurs later, after discovery of the delamination. Accomplishment of this modification constitutes terminating action for the inspections required by paragraphs A. and B. of this AD. \n\n\tE.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\tF.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tAirworthiness Directive 91-07-04 supersedes AD 89-15-05, Amendment 39-6264. \n\n\tThis amendment (39-6933, AD 91-07-04) becomes effective on April 15, 1991.
2022-18-01: The FAA is superseding Airworthiness Directive (AD) 2017-10- 24, which applied to certain Airbus SAS Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330- 300 series airplanes; AD 2018-23-14, which applied to certain Airbus SAS Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes; and AD 2021-05-12, which applied to certain Airbus SAS Model A330-200 Freighter series airplanes. AD 2017-10-24, AD 2018-23-14, and AD 2021-05-12 require revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD revises the applicability by adding airplanes. This AD continues to require the actions in AD 2018-23-14 and AD 2021-05-12, and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness 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.
2022-17-13: The FAA is adopting a new airworthiness directive (AD) for certain Piaggio Aero Industries S.p.A. (Piaggio) Model P-180 airplanes. This AD is prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as altimetry system errors in the air data computers (ADCs) and stand-by instrument systems. This AD requires amending the existing airplane flight manual (AFM), installing improved ADCs and a detachable configuration module (DCM), and revising the existing instructions for continued airworthiness. The FAA is issuing this AD to address the unsafe condition on these products.
90-14-09: 90-14-09 SHORT BROTHERS: Amendment 39-6649. Docket No. 90-NM-128-AD. Applicability: Model SD3-60 series airplanes, Serial Numbers SH3601 through SH3642, inclusive, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the wings, accomplish the following: A. Upon the accumulation of 9,600 hours time-in-service or within 30 days after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 600 hours time-in-service, perform the following inspections: 1. For airplanes with Serial Numbers SH360l through SH3635, inclusive: Perform a visual inspection of the left and right outerwing/strut attachment fittings in accordance with Short Brothers Service Bulletin SD360-57-12, dated June 8, 1990. 2. For airplanes with Serial Numbers SH3601 through SH3642, inclusive: Perform a visual inspection of the left and right stub wing/strut attachment fittings in accordance with Short Brothers Service Bulletin SD360-57-12, dated June 8, 1990. B. If cracks are found, prior to further flight, repair or replace with serviceable part in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. C. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. 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. All persons affectedby this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Short Brothers, PLC, Service Representative, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6649, AD 90-14-09) becomes effective on July 23, 1990.
91-07-12: 91-07-12 BRITISH AEROSPACE: Amendment 39-6950. Docket No. 90-NM-273-AD. Applicability: All Model DH/BH/HS 125 series airplanes, post-modification 255640, certificated in any category. Compliance is required as indicated, unless previously accomplished. To ensure proper operation of the main landing gear (MLG) door, accomplish the following: A. Prior to the accumulation of 6,000 landings on the right and left MLG door aluminum forward hinge fittings, or within the next 400 landings after December 4, 1990 (the effective date of Amendment 39-6786, AD 90-23-01), whichever occurs later, and thereafter at intervals not to exceed 6,000 landings, replace the aluminum forward hinge fittings in accordance with British Aerospace Service Bulletin 32-218, dated July 28, 1988. B. Replacement of an aluminum hinge fitting with a new stainless steel hinge fitting, in accordance with British Aerospace Service Bulletin 32-220-3176A, B, and C, dated September 2, 1988, terminates the requirements for the replacement of the hinge fittings required by paragraph A. of this AD. 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. 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. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 91-07-12 supersedes AD 90-23-01, Amendment 39-6786. This amendment (39-6950, AD 91-07-12) becomes effective on April 29, 1991.
2004-20-02: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 707 and 720 series airplanes, that requires an inspection of the main landing gear (MLG) lock support fitting and the wing fillet flap support link for damage, and corrective action, if necessary; and replacement of the bolts and bushings at the joint between the MLG lock support fitting and the wing fillet flap support link. This action is necessary to prevent stress corrosion cracking of the bolts and wearing of the joint between the lock support fitting and the support link, which could lead to failure of the joint and could cause the collapse of the MLG. This action is intended to address the identified unsafe condition.
2013-12-05: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model MBB-BK 117 C-2 helicopters. This AD requires determining if a certain serial-numbered bevel gear is installed in the tailrotor intermediate gear box (IGB). If such a bevel gear is installed in the IGB, this AD requires recording the bevel gear's reduced life limit in the Airworthiness Limitations section of the maintenance manual and on the component history card or equivalent IGB record. If the bevel gear's life limit has been reached or exceeded, this AD requires, before further flight, replacing the bevel gear with an airworthy bevel gear. This AD is prompted by the discovery that the tooth foot fillets in certain bevel gears fall below the minimum dimensions required in the design documents to ensure safe functioning of the bevel gear until it reaches its approved life limit. This AD's actions are intended to prevent failure of a bevel gear before it reaches its currentlyapproved life limit, failure of the IGB, and subsequent loss of helicopter control.
96-25-15: This amendment adopts a new airworthiness directive (AD), applicable to certain transport category airplanes equipped with certain Honeywell Standard Windshear Detection System (WSS). It requires a revision to the airplane flight manual to alert the flightcrew of the potential for significant delays in the WSS detecting windshear when the flaps of the airplane are in transition. This amendment also requires replacement of the currently-installed line replaceable unit (LRU) with a modified LRU having new software that eliminates delays in the WSS. This amendment is prompted by a report of an accident during which an airplane encountered severe windshear during a missed approach. The actions specified by this AD are intended to prevent significant delays in the WSS detecting hazardous windshear, which could lead to the loss of flight path control.
2022-18-16: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) CT7-8A model turboshaft engines. This AD was prompted by the manufacturer revising the airworthiness limitations section (ALS) of the existing engine maintenance manual (EMM) to incorporate reduced life limits for certain stage 1 turbine aft cooling plates, stage 2 turbine forward cooling plates, turbine interstage seals, and stage 4 turbine disks. This AD requires revising the ALS of the existing EMM and the operator's existing approved maintenance or inspection program, as applicable, to incorporate reduced life limits for these parts. The FAA is issuing this AD to address the unsafe condition on these products.
91-06-18: 91-06-18 AIRBUS INDUSTRIE: Amendment 39-6940. Docket No. 90-NM-225-AD. Applicability: All Model A310-200 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks in the wing rear spar and prevent reduced structural integrity of the wings, accomplish the following: A. Prior to the accumulation of 12,000 landings, or within 1,000 landings after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) rototest inspection of the wing rear spar at certain bolt holes where the main landing gear (MLG) forward pick-up fittings are attached to the rear spar, in accordance with Airbus Industrie Service Bulletin A310-57-2046, dated March 5, 1990. 1. If no cracks are found at the first inspection and no cold working of the holes concerned is carried out, repeat the HFEC rototest inspection at intervals not to exceed 4,500 landings. 2. If no cracksare found at the first inspection and a spar life extension by cold working of the holes concerned is carried out in accordance with the paragraph 2.3.(1)(b) of the Accomplishment Instructions of the above service bulletin or Airbus Industrie Service Bulletin A310-57-2049, dated April 10, 1990; repeat the HFEC rototest inspection within the next 18,000 landings, and thereafter at intervals not to exceed 12,000 landings. B. If cracks are found, repair prior to further flight, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Repeat the HFEC rototest inspection at an interval approved by the Manager, Standardization Branch, ANM-113. C. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to theManager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6940, AD 91-06-18) becomes effective on April 22, 1991.
96-21-13: This amendment adopts a new airworthiness directive (AD) that is applicable to LITEF GmbH Attitude and Heading Reference System (AHRS) Unit Model LCR-92, LCR-92S, and LCR-92H installed on but not limited to Sikorsky Aircraft Model S-76 helicopters, McDonnell Douglas Helicopter Systems Model MD-900 helicopters, Bell Helicopter Textron, Inc. Model 412 helicopters, and Pilatus Model PC-12 airplanes. This action requires either installing a placard adjacent to each primary attitude indicator which states that flight is limited to Visual Flight Rules (VFR) operations only, or modifying and inspecting the AHRS wiring cables, requiring a repetitive inspection of the cable shielding, and inserting a statement into the aircraft flight manual. This amendment is prompted by a field report and verified by laboratory tests that shows there is an unusual AHRS reaction to certain radio frequency signals. The actions specified by this AD are intended to prevent reliance on or to correct the cause of misleading roll and pitch information produced by the AHRS when encountering certain radio frequency signals.
2004-20-03: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-8-101, -102, -103, -106, -201, - 202, -301, -311, and -315 airplanes. This amendment requires a detailed inspection of the wing leading edge de-icer boots to determine if they comply with certain patch limits in the critical zone; and corrective action, if necessary. This action is necessary to prevent reduced aerodynamic smoothness of the wing leading edge de-icer boots and possible reduced stall margin, which could result in a significant increase in stall speeds, leading to a possible stall prior to activation of the stall warning. This action is intended to address the identified unsafe condition.