Results
88-06-07: 88-06-07 GENERAL ELECTRIC: Amendment 39-5866. Applies to General Electric (GE) CF34-1A and -3A turbofan engines installed in the Canadair Limited Model CL-600-2A12 and CL-600-2B16 aircraft. Compliance is required as indicated, unless already accomplished. To prevent an engine flameout or uncommanded power roll-back and subsequent inflight shutdown due to contamination of the fuel control, accomplish the following: (a) For the engines not operated in accordance with Canadair Airplane Flight Manual (AFM) Temporary Revision Numbers 601/10-1 and 601/11 for Model CL-600-2B16, or Temporary Revision Numbers 601/17-1 and 601/18 for Model CL-600-2A12, accomplish the following prior to further flight after the effective date of this AD: (1) For engines with fuel controls identified in GE Service Bulletin (SB) Number (CF34) 73-5, dated January 22, 1988, replace the fuel control with a reworked unit which has a redesigned bypass valve piston installed and cleaned internally by the improved process, in accordance with this SB. (2) For engines with fuel controls identified in GE SB Number 73-6, dated January 22, 1988, replace the bypass valve piston with redesigned hardware in accordance with this SB. (b) For the engines operated in accordance with Canadair AFM Temporary Revisions Numbers 601/10-1 and 601/11 for Model CL-600-2B16, or Temporary Revision Numbers 601/17-1 and 601/18 for Model CL-600-2A12, accomplish paragraphs (a)(1) and (a)(2) above within 500 hours in service from the effective date of this AD, or prior to September 30, 1988, whichever occurs sooner. (c) Aircraft may be ferried in accordance with the provision of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon request, an equivalent means of compliance with the requirements of the AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. (e) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance times specified in this AD. The GE SB's identified and described in this document are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received the engine manufacturer's SB's may obtain copies upon request to General Electric Company, 1000 Western Avenue, Lynn, Massachusetts 01910. These documents also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 88-ANE-08, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment becomes effective on March 23, 1988.
2017-24-04: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.27 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by reports indicating that certain exit signs have a hydrogen isotope that decays over time, causing the signs to lose their brightness. We are issuing this AD to address the unsafe condition on these products.
2017-23-08: We are superseding Airworthiness Directive (AD) 2014-24-02 for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters. AD 2014-24-02 required repetitively inspecting the main rotor (M/R) rotating scissors, removing certain lower half scissor spherical bearings (bearings) from service, and installing a special nut. This new AD revises the inspection requirements and requires replacing the bearings. This AD is prompted by a new report of a dislodged bearing of an M/R rotating scissor. The actions of this AD are intended to correct an unsafe condition on these products.
2002-03-01: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc., and Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, and former military T53-L-11, T53-L-11A, T53-L-11B, T53-L-11C, T53-L-11D, T53-L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-13B S/SB, and T53-L-703 series turboshaft engines. This amendment requires initial and repetitive special vibration tests of the engine, and if necessary replacement with a serviceable reduction gearbox assembly, or a serviceable engine before further flight. This amendment is prompted by reports of tachometer drive spur gear failure, resulting in potential engine overspeed, loss of power turbine speed (N2) instrument panel indication, and hard landings. The actions specified in this AD are intended to prevent excessive vibrations produced by the reduction gearbox assembly that could cause failure of the tachometer drive spur gear.
2017-23-04: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600R series airplanes; Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R airplanes. This AD was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which indicates that cracks may develop in adjacent stringers at the same time. This AD requires an inspection of the upper wing skin and top stringer joints, and modification of the stringer joint couplings if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-23-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of crack indications in the right wing upper aft skin, originating from fastener holes common to the rear spar upper chord. This AD requires repetitive inspections for cracking of the wing upper aft skin, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2005-17-01: The FAA adopts a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. (Pilatus) (also identified as Fairchild Republic Company and Fairchild Heli Porter) Model PC-6 airplanes. This AD requires you to repetitively inspect the stabilizer-trim attachment and structural components for cracks, corrosion, and discrepancies and replace any defective part with a new part. This AD also requires you to replace all Fairchild connecting pieces, part number (P/N) 6232.0026.XX, with a Pilatus connecting piece and requires you to replace fittings without an index after the P/N with an improved part. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct defective stabilizer-trim attachments and surrounding structural components, which could result in failure of the stabilizer-trim attachment. This failure could lead to loss of control of the airplane.
84-20-02: 84-20-02 CESSNA: Amendment 39-4922. Applies to Models 402C (S/Ns 402C0001 thru 402C0802); 404 (S/Ns 404-0001 thru 404-0859); 414A (S/Ns 414A0001 thru 414A1003); 421C (S/Ns 421C0001 thru 421C1402); 425 (S/Ns 425-0002 thru 425-0190); 441 (S/Ns 441-0001 thru 441-0333) airplanes certificated in any category. Compliance: Required within the next 200 hours time-in-service after the effective date of this AD, unless already accomplished. To preclude collapse of the nose landing gear: (a) Replace the nose landing gear actuator rod ends on Models 425 and 441 airplanes in accordance with Cessna Service Information Letter (CSIL) PJ84-10 dated March 2, 1984, and on Models 402C, 404, 414A and 421C airplanes in accordance with CSIL ME84-10 dated March 9, 1984. (b) The aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, Federal Aviation Administration, Room 100, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4400. This amendment becomes effective on November 1, 1984.
82-06-12: 82-06-12 AIR TRACTOR: Amendment 39-4350. Applies to Models AT-300 (S/Ns 300-0001 through 300-9999); AT-301 (S/Ns 301-0001 through 301-9999); AT-302 (S/Ns 302-0001 through 302-9999); AT-400 (S/Ns 400-0244 through 400-9999); and AT-400A (S/Ns 400A-0397 through 400A-9999) airplanes certified in any category and equipped with 1-inch-thick (P/N 40007-2 or P/N 40058-1) main landing gear struts. COMPLIANCE: Required as indicated, unless already accomplished. To prevent possible failure of the P/N 40007-2 or P/N 40058-1 main landing gear struts accomplish the following: (a) Models AT-300 and AT-301 airplanes: (1) On struts having exceeded, or upon accumulating, 1,000 hours time-in- service or 5,000 landings, whichever occurs first, within 20 hours time-in-service or 100 landings, whichever occurs first, after the effective date of this AD and thereafter at intervals of 100 hours time-in-service or 500 landings, whichever occurs first, inspect and replace as necessary the landing gear struts in accordance with paragraph (c). (2) On struts having exceeded, or upon accumulating, 2,000 hours time-in- service or 7,500 landings, whichever occurs first, prior to further flight, replace the struts with new struts of the same part number. (b) Models AT-302, AT-400 and AT-400A airplanes: (1) On struts having exceeded, or upon accumulating, 600 hours time-in- service or 3,000 landings, whichever occurs first, within 20 hours time-in-service or 100 landings, whichever occurs first, after the effective date of this AD and thereafter at intervals of 100 hours time-in-service or 500 landings, whichever occurs first, inspect the struts and replace as necessary in accordance with paragraph (c). (2) On struts having exceeded, or upon accumulating, 1,200 hours time-in- service, or 6,000 landings, whichever occurs first, prior to further flight, replace the struts with new struts of the same part number. (c) Remove the left and right outboard fuselage clamp blocks. Remove all minor corrosion on both main landing gears by sandblasting. Inspect both main landing gears using dye penetrant or magnetic particle inspection procedures with special attention in the areas of strut contact with the clamp blocks. Replace all parts which are damaged, cracked, or have severe corrosion pitting with new parts of the same part number before further flight. All struts returned to service must be painted. (d) The aircraft hours and landings may be used as the time-in-service or landings on the struts if time-in-service or landings on the struts cannot be established by the airplane maintenance records. (e) A special flight permit may be issued in accordance with FAR 21.197 to allow flight of the aircraft to a location where this AD can be accomplished. (f) An equivalent method of compliance with this AD may be used when approved by the Chief, Aircraft Certification Division, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76101. Snow Engineering Company Service Letter No. 45, dated November 1, 1981, covers the subject matter of this AD. Compliance with this Service Letter within the last 100 hours time-in-service or 500 landings, whichever comes first, satisfies the initial inspection requirement of paragraphs (a) and (b) of this AD. This amendment becomes effective on March 25, 1982.
92-08-51: 92-08-51 TEXTRON LYCOMING: Amendment 39-8344. Docket 92-ANE-13. Applicability: Textron Lycoming Model ALF502R series turbofan engines installed on British Aerospace BAe-146 airplanes. Compliance: Required as indicated, unless accomplished previously. To prevent uncommanded in-flight engine power reduction of engines during inclement weather or icing conditions, accomplish the following: (a) Replace the existing engine fuel control, Part Number (P/N) 2-163-810-07, 2-163-810-12, or 2-163- 810-15 with an improved fuel control, P/N 2-163-810-20, 2-163-810-21, or 2-163-810-23, or rework the existing engine fuel control, in accordance with Textron Lycoming Alert Service Bulletin (ASB) No. A-ALF 502R 73-12, Revision 1, dated April 7, 1992, at the first maintenance access of the engine fuel control or within 300 operating cycles after the effective date of this AD, whichever occurs first. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office, FAA, Engine and Propeller Directorate. The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The replacement or rework of the engine fuel control shall be done in accordance with the following Textron Lycoming Alert Service Bulletin (ASB): Document No. Pages Version Date Textron Lycoming 1,2,4,5 Rev. 1 April 7, 1992 ASB A-ALF-502R 73-12 3,6,7,8 Original April 1, 1992 Total pages: 8This 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 Textron Lycoming, Stratford Division, 550 Main Street, Stratford, Connecticut 06497. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC 20001. (e) This amendment becomes effective on March 18, 1993, to all persons except those persons to whom it was made immediately effective by telegraphic AD T92-08-51, issued April 8, 1992, which contained the requirements of this amendment.
2023-04-05: The FAA is superseding Airworthiness Directive (AD) 2022-09- 11, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2022-09-11 required 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 continues to require the actions in AD 2022-09- 11 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.
2023-04-02: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace LP Model Gulfstream G280 airplanes. This AD was prompted by a determination that the existing wet runway performance tables in the airplane flight manual (AFM) may not provide an acceptable level of safety. This AD requires revising the existing AFM to incorporate new wet runway performance tables, as specified in a Civil Aviation Authority of Israel (CAAI) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2002-02-13: This amendment adopts a new airworthiness directive (AD), that is applicable to CFM International, S.A. (CFMI) CFM56-5 series turbofan engines. This amendment requires replacement of the magnetic drain plug on certain part number (P/N) air turbine engine starters manufactured by Honeywell Engines & Systems. This amendment is prompted by three instances of uncontained air turbine engine starter failures, resulting in cowl damage. The actions specified by this AD are intended to prevent uncontained failure of the starter and possible damage to the airplane.
93-14-05: 93-14-05 BRITISH AEROSPACE: Amendment 39-8629. Docket 92-NM-138-AD. Supersedes AD 77-17-10 R2, Amendment 39-4713. Applicability: All Model BAC 1-11-200 and -400 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent unannunciated failure of the wing flap secondary drive shafts, accomplish the following: (a) Within 300 hours time-in-service after the effective date of this AD, unless previously accomplished within the last 900 hours time-in-service prior to the effective date of this AD: Open the left and right spoilers and perform an inspection, visually (detailed visual inspection) and by feel, of the visible wing flap secondary drive shafts to detect failure or damage, in accordance with paragraph 2.4 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 4, dated May 6, 1991. Prior to further flight, repair or replace any defective shafts in accordance with paragraphs (c)(2) and (e) of this AD. (b) Within 1,200 hours time-in-service after the effective date of this AD: Perform a general visual inspection of all wing flap secondary drive shafts to detect failure or damage, in accordance with paragraph 2.1 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981, or paragraph 2.1.2 of Issue 4, dated May 6, 1991. (1) Repeat the general visual inspections thereafter at intervals not to exceed 1,200 hours time-in-service. (2) If any shaft is found that is distorted or chafed, prior to further flight, perform an inspection of that shaft, visually (detailed visual inspection) and by feel, in accordance with paragraph 2.4 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981, or Issue 4, dated May 6, 1991. Shafts that fail to meet the inspection specifications listed in paragraph 2.4 of the service bulletin must be replaced,prior to further flight, in accordance with paragraph 2.4.1 of the service bulletin. (c) For spanwise wing flap secondary drive shafts between wing station 0 and wing rib 14: Prior to the accumulation of 3,600 total hours time-in-service or within the next 1,200 hours time-in-service after the effective date of this AD, whichever occurs later, perform an inspection, visually (detailed visual inspection) and by feel, to detect failure or damage, in accordance with paragraph 2.4 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981, or Issue 4, dated May 6, 1991. (1) Repeat the inspection thereafter at the times specified in paragraphs (c)(1)(i) and (c)(1)(ii) of this AD: (i) For spanwise wing flap secondary drive shafts that have accumulated less than 24,000 total hours time-in-service: At intervals not to exceed 3,600 hours time-in-service or 24 months, whichever occurs earlier. (ii) For spanwise wing flap secondary drive shafts that have accumulated 24,000 or more hours time-in-service: At intervals not to exceed 2,400 hours time-in-service or 24 months, whichever occurs earlier. (2) Shafts that fail to meet the specifications listed in paragraph 2.4 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981, or Issue 4, dated May 6, 1991, must be replaced, prior to further flight, in accordance with paragraph 2.4.1 of the service bulletin. (d) For wing flap secondary drive shafts located between wing station 0 and wing rib 14, listed in Appendix 1 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 4, dated May 6, 1991, on which Modification PM5341/HCA929 is applicable, but has not been accomplished: Prior to the accumulation of 30,000 total hours time-in-service, or within 1,000 hours time-in-service after the effective date of this AD, whichever occurs later; overhaul and modify the wingflap secondary drive shafts by installing British Aerospace Modification PM5341, in accordance with paragraph 2.3 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981, or Issue 4, dated May 6, 1991. At overhaul, the shaft tubing must be replaced with Modification PM5341 improved tubing, but serviceable end fittings may be reused. (e) Whenever replacing or repairing a flap secondary drive shaft in accordance with paragraph (a), (b) or (c) of this AD, or whenever overhauling a wing flap secondary drive shaft in accordance with paragraph (d) of this AD, inspect the adjacent shaft support bearings for excessive radial play, in accordance with Section 27-52-00 of the BAC 1-11 Maintenance Manual. Prior to further flight, replace any shaft support bearings having radial play in excess of 0.020 inch total indicated reading with a serviceable bearing. (f) Operators who have not kept records of hours time-in-service on individualwing flap secondary drive shafts shall substitute airplane hours time-in-service in lieu thereof. (g) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (h) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (i) The inspections, replacement, overhaul, and modification shall be done in accordance with British Aerospace BACOne-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981; and British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 4, dated May 6, 1991; as applicable. This 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (j) This amendment becomes effective on August 23, 1993.
56-06-01: 56-06-01 CONTINENTAL: Applies to O-470 Series and E Series Engine Serial Numbers Below Excepting Any Remanufactured Engine Shipped From Continental Motors Corp. After May 1, 1955, and Engine Serial Numbers Designated "Exceptions." Compliance required as soon as possible but not later than July 1, 1956. To prevent serious engine damage in flight, the following must be accomplished: 1. Replace present piston pin assembly with piston pin assembly P/N 539467 in the following serially numbered engines: Engine Model O-470-A, Serial Nos. 41258 to 41679, 40015-2-A, 40021-2-A, 40028-2-A, 40045-2-A, 40054-2- A, 40074-3-A, 40110-3-A, 40125-3-A, 40154-3-A, 40168-3-A, 40176-3-A, 40177-3-A, 40203-3-A, 40204-3-A, 40242-3-A, 40264-3-A, 40267-3-A, 40293-3-A, 40334-3-A, 40371-3-A, 40418-3-A, 40424-3-A, 40438-3-A, 40444-3- A, 40485-3-A, 40494-3-A, 40567-3-A, 40579-3-A, 40581-3-A, 40601-3-A, 40619-3-A, 40647-3-A, 40651-3-A, 41008-3-A, 41025-3-A, 41032-3-A, 41033-3-A, 41038-3-A, 41039-3-A, 41068-3-A, 41094-3-A, 41109-4-A, 41175-4- A, 41181-4-A, 41187-4-A, 41189-4-A, 41196-4-A, 41251-4-A, 41254-4-A. Engine Model O-470-B, Serial Nos. 50001 to 50256. Exceptions - 50189, 50241, 50245, 50246, 50247, 50250, 50251, 50252. Engine Model O-470-J, Serial Nos. 45001 to 45533. Exceptions - 45520, 45521, 45525, 45529. Engine Models E-225-4, E-225-8, Serial Nos. 30163 to 30715. Engine Models E-185-8, E-185-11, Serial Nos. 22200 to 22269. Engine Model E-185-9, Serial Nos. 6128 to 6135. In addition, replace piston pin assembly, P/N 535145, with piston pin assembly, P/N 539467, in any O-470 or E Series engine that was overhauled in the field and in which it is known that P/N 535145 was installed at time of overhaul. (Continental Motors Corp. Service Bulletin No. M56-2, Supplement No. 1, dated March 12, 1956, further discusses this subject.) 2. Replace present oil pump gear assembly with oil pump gear assembly P/N 539525 in the following serially numbered engines: Engine Model O-470-B, Serial Nos. 50076 to 50256. Exceptions - 50189, 50241, 50245, 50246, 50247, 50250, 50251, 50252. Engine Model O-470-J, Serial Nos. 45001 to 45533. Exceptions - 45447, 45448, 45456, 45457, 45462, 45463, 45466, 45468, 45473, 45474, 45481, 45484, 45489, 45491, 45494, 45495, 45500, 45503, through 45514, 45516, 45519, 45520, 45522, 45523, 45525, 45526, 45528, 45529, 45532. 3. Replace present exhaust valve with exhaust valve P/N 539449 in the following serially numbered engines: Engine Model O-470-A, Serial Nos. 40001 to 40673. Engine Model O-470-A, Serial Nos. 41001 to 41679. Engine Model O-470-J, Serial Nos. 45001 to 45489. Exception - 45487. (Continental Motors Corp. Service Bulletin M56-2, dated February 14, 1956, further discusses this subject and offers special discounts for replacement parts ordered prior to July 1, 1956, from bona fide Continental aircraft engine spare parts distributors.)
2017-21-06: We are adopting a new airworthiness directive (AD) for certain 328 Support Services GmbH Model 328-100 and Model 328-300 airplanes. This AD was prompted by reports of broken bonding wires of certain fuel line clamps. This AD requires repetitive inspections of certain fuel line clamps for discrepancies; repetitive inspections of certain parts for chafing marks; and replacement of any discrepant parts. This AD also includes an optional modification, which is a terminating action for the inspections. We are issuing this AD to address the unsafe condition on these products.
2017-22-09: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model SAAB 340B airplanes. This AD was prompted by reports of natural stall events in icing conditions, without prior stall warnings. This AD requires modifying the stall warning system, installing new stall warning computers, and activating the stall warning system. We are issuing this AD to address the unsafe condition on these products.
2002-03-02: This amendment supersedes Airworthiness Directive (AD) 98-13-03, which currently requires repetitive inspections of the main landing gear (MLG) hinge fittings, support angles, and attachment bolts on British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, and Jetstream Series 3101 airplanes. AD 98-13-03 also requires eventual installation of improved design MLG hinge fittings as terminating action for the repetitive inspections of the hinge fittings and attachment bolts. AD 98-13-03 specifies repetitive inspections of the support angles for those airplanes with the improved design MLG hinge fittings installed and exempts from the applicability those airplanes with the improved design MLG hinge fittings installed. This AD retains the requirements of AD 98-13-03 and removes the applicability exemption of those Model HP.137 Jetstream Mk.1 and Jetstream Series 200 airplanes with the improved design MLG hinge fittings installed. The actions specified by this AD are intended to detect, correct, and prevent future fatigue cracking of the MLG, which could result in structural failure of the MLG and consequent loss of airplane control during takeoff, landing, or taxi operations.
2023-04-03: The FAA is adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by reports of cracks at the upper and lower fastener holes of a repair plate in the stubwing, which had been applied to repair heat damage. This AD requires a one-time inspection of the fuselage skin in the stubwing bay area to determine if a heat damage repair plate is installed, an inspection of repaired areas for cracking, and applicable corrective actions, 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.
2010-02-05: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2010-02-05 that was sent previously by individual notices to the known U.S. owners and operators of affected airplanes identified above. This AD requires modifying the flight deck door. This AD was prompted by a report indicating that certain equipment of the flight deck door is defective. We are issuing this AD to prevent failure of this equipment, which could jeopardize flight safety.
2005-16-08: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires repetitively replacing and testing a certain relay in the passenger oxygen release system in the forward cabin. This AD results from reports of a failed relay in the passenger oxygen release system. We are issuing this AD to prevent failure of the relay, which could result in the oxygen masks failing to deploy and deliver oxygen to the passengers in the event of a rapid decompression or cabin depressurization.
87-26-03: 87-26-03 BOEING: Amendment 39-5803. Applies to Model 737 series airplanes, specified in Boeing Service Bulletin 737-34A1208, Revision 1, dated May 14, 1987, certificated in any category. Compliance required within the next year after the effective date of this AD, unless previously accomplished. \n\n\tTo minimize the possibility of misleading localizer deviation indication to the flight crew caused by electromagnetic interference, accomplish the following: \n\n\tA.\tReplace the existing weather radar receiver-transmitters with modified receiver- transmitters; install 10 db attenuators in line with the localizer coaxial cables; if Bendix VHF navigation receivers are installed, replace with modified receivers; and, for Model 737-300 airplanes equipped with electronic flight instrument system (EFIS), modify specific wire bundles and their routing, in accordance with Boeing Service Bulletin 737-34A1208, Revision 1, dated May 14, 1987, or later FAA-approved revision.\n \n\tB.\tAn alternatemeans 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\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification required by 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 Company, P.O. Box 3707, Seattle, Washington 98124-2207. These documents 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. \n\n\tThis amendment becomes effective February 1, 1988.
2002-02-07: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330 and A340 series airplanes, that requires repetitive inspections and operational checks of the spring function of the emergency exit door slider mechanism, and corrective action if necessary. This action is necessary to prevent failure of the spring locking function of the slider mechanism due to corrosion, which could result in the escape slide detaching from the airplane in an emergency evacuation. This action is intended to address the identified unsafe condition.
2002-02-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and A300 B4; A300 B4-600, B4-600R, and F4-600R (collectively called A300-600); and A310 series airplanes. This AD requires repetitive overhaul, including associated modifications, of the ram air turbine (RAT). This action is necessary to prevent failure of the RAT to deploy or operate properly in the event of an emergency, which could result in reduced hydraulic pressure or electrical power on the airplane. This action is intended to address the identified unsafe condition.
92-20-03: 92-20-03 BRITISH AEROSPACE: Amendment 39-8377. Docket No. 92-NM-98-AD. Applicability: Model DH/HS 125 series airplanes; as listed in British Aerospace Service Bulletin SB 57-76, dated December 31, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of structural integrity and possible collapse of the main landing gear (MLG) on landing or take-off, accomplish the following: (a) Within 12 months after the effective date of this AD, perform a one-time visual inspection to detect corrosion on the MLG support brackets, rear spar sections, inboard flap hinge arms, and associated attachment hardware, in accordance with British Aerospace Service Bulletin SB 57-76, dated December 31, 1991. (b) If no corrosion is found on the MLG support brackets, rear spar sections, inboard flap hinge arms, and associated attachment hardware, no further action is necessary. (c) If any corrosion is found on the MLG support brackets, rear spar sections, and inboard flap hinge arms, prior to further flight, replace any corroded parts found, or repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (d) If corrosion is found on any associated attachment hardware that is within the limitations specified in the Structural Repair Manual (SRM) Chapter 51 10, prior to further flight, replace or repair in accordance with the SRM. (e) If corrosion is found on any associated attachment hardware that is beyond the limitations specified in the Structural Repair Manual (SRM) Chapter 51 10, prior to further flight, replace or repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA,Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (g) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (h) The inspection shall be done in accordance with British Aerospace Service Bulletin SB 57-76, dated December 31, 1991. This 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC. 20041-0414.Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on November 17, 1992.