Results
2019-16-02: The FAA is adopting a new airworthiness directive (AD) for all GE Honda Aero Engines (GHAE) HF120 model turbofan engines with a certain fuel pump metering unit (FPMU) assembly. This AD was prompted by damage found on the permanent magnetic alternator (PMA) drive gear within the FPMU assembly. This AD requires removal of a certain FPMU assembly and its replacement with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
98-19-15: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-19-15, which was sent previously to all known U.S. owners and operators of Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes. The AD applies to those airplanes that are equipped with Barber-Colman pitch trim actuators, part number (P/N) 27-19008-001 or P/N 27-19008-002. This AD requires incorporating information into the Limitations Section of the airplane flight manual (AFM) that imposes a speed restriction and a minimum pilot requirement. The AD resulted from reports of two incidents of abrupt movement of the horizontal stabilizer to or near the full airplane nose-up position. These two incidents involved mechanical failure of these Barber-Colman pitch trim actuators. The actions specified by this AD are intended to lessen the severity of airplane pitch up caused by mechanical failure of the pitch trim actuator, which could result in a pitch upset and structural failure of the airplane.
2007-03-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracking of the wing MLG (main landing gear) rib 6 aft bearing forward lugs, which could result in reduced structural integrity of the MLG attachment. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
88-13-08: 88-13-08 PARTENAVIA COSTRUZIONE AERONAUTICHE S.p.A: Amendment 39-5953. Applies to models P 68, P 68B, P 68C, P 68C-TC, P 68 "Observer", and P 68-TC "Observer" (all serial numbers (S/N)) airplanes certificated in any category. Compliance: Required initially within 6 calendar months after the effective date of this AD unless already accomplished within the last 24 calendar months preceding the effective date of this AD, and thereafter at intervals not to exceed 24 calendar months or 500 hours time-in- service, (TIS) whichever occurs first, unless already accomplished. To prevent engine mount failure, whirl mode flutter, and structural failure of the wing, accomplish the following: (a) For S/N 1 thru 368, at the time of the initial inspection specified in this AD, modify the engine skin panels for inspection access in accordance with the instructions in Section 1 of Partenavia Service Bulletin (S/B) No. 70, Rev. 1, dated May 13, 1987. (b) For S/N 1 thru 368, visually inspect the upper and lower engine mounts and attachments for surface corrosion and cracks in accordance with the instructions in Section 1 of the above S/B. If cracks or surface corrosion are found, prior to further flight repair the affected structure in accordance with the instructions in paragraph (d) of this AD. (c) For S/N 369 and subsequent, visually inspect the upper and lower engine mounts and attachments for surface corrosion and cracks in accordance with the instructions in Section 3 of the above S/B. If cracks or surface corrosion are found, prior to further flight repair the affected structure in accordance with the instructions in paragraph (d) of this AD. (d) If cracks or surface corrosion are found as a result of the inspections specified in paragraphs (b) or (c) of this AD, prior to further flight, repair the affected structure as follows: (1) If the surface corrosion or crack extends no deeper than 75/1000 (7.5 percent) of the original local thickness, so that no less than 92.5 percent of the original local thickness remains, repair using the procedures described in Section 1 of Partenavia S/B No. 70, Rev. 1, dated May 13, 1987. (2) If any crack or surface corrosion extends deeper than 75/1000 (7.5 percent) of the original local thickness, so that less than 92.5 percent of the original local thickness remains including blistering, pitting, or flaking, prior to further flight, remove and replace the affected part with a serviceable part as described in Section 2 of Partenavia S/B No. 70, Rev. 1, dated May 13, 1987. (e) Within one week following each inspection specified in paragraph (b) or (c) of this AD, submit a written report of the result of that inspection to include whether or not damage was found, part number(s) involved, extent, location, and description of any damage found, and a brief description of remedial measures. Submit the reports to the FAA, ACE-109, 601 East 12th Street, Kansas City, Missouri 64106.If an inspection was made previous to this AD, forward the requested data within one week of receipt of this AD. (Report approved by the Office of Management and Budget under OMB No. 2120-0056.) (f) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (g) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000, Brussels, Belgium; Telephone (322) 513.3830 ext. 3710/2711. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Partenavia Costruzione Aeronautiche, S.p.A., Via Cava, Casoria-Naples, Italy; Telephone 81 759-0946 (Product Support); or may examine these documents at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-5953, becomes effective onJuly 13, 1988.
2000-26-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 and A300-600 series airplanes, that currently requires wiring modifications to the engine and auxiliary power unit (APU) fire detection system. This amendment requires new wiring modifications for the engine and APU fire detection system. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the fire warning from terminating prematurely, which could result in an unnoticed, uncontained engine/APU fire.
2019-14-10: The FAA is superseding Airworthiness Directive (AD) 2018-02- 11, which applies to certain Airbus SAS Model A330-301, -321, -322, and -342 airplanes. AD 2018-02-11 requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. Since the FAA issued AD 2018-02-11, the agency received a report of additional cracking found on different airplane models, and of an update to the fatigue and damage tolerance analysis. This AD requires repetitive detailed inspections of the horizontal stabilizer (HS) center box (CB) top skin integral flange area, and repair if necessary. This AD also expands the applicability to include additional airplane models. The FAA is issuing this AD to address the unsafe condition on these products.
2007-01-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310-300 airplanes. This AD requires replacing the existing non-return valve (NRV) of the auxiliary center tanks (ACTs) of the fuel system with a new, improved NRV. This AD results from a report that it was not possible to transfer fuel from ACTs 1 and 2 during flight, and no electronic centralized aircraft monitor warnings were triggered. Investigation revealed a faulty static inverter and blown fuse, resulting in failure of certain fueling bus bars and subsequent failure of the automatic ACT fuel transfer. We are issuing this AD to prevent these failures, combined with failure of the NRV to close. If the NRV is open during flight, the fuel supply to the engines may be reduced during cross-feed operation to the extent that fuel starvation could occur and result in engine flameout.
2007-01-12: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Model Mystere-Falcon 50 and 900, and Falcon 900EX airplanes; and Model Falcon 2000 and Falcon 2000EX airplanes. This AD requires an inspection of the identification plates of the outboard slats to determine the type of identification plates and the part numbers. For certain airplanes, this AD also requires a revision to the Limitations and Normal Procedures sections of the airplane flight manual to provide procedures for operation in icing conditions; and replacement of the anti-icing manifold with an anti-icing manifold of the correct type design if necessary. For certain airplanes, this AD also requires related investigative and corrective actions if necessary. This AD results from a finding that the outboard slats for Model Mystere-Falcon 50 airplanes have been erroneously authorized, in limited cases, as interchangeable for use on Model Mystere-Falcon 900 and Falcon 900EX airplanes; and Model Falcon 2000 and Falcon 2000EX airplanes. We are issuing this AD to prevent failure of the anti-icing manifold of the outboard slats, which could result in loss of control of the airplane.
2007-01-14: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires revising the Airworthiness Limitations Items (ALI) of the maintenance requirements manual to require additional inspection requirements of the maintenance requirements manual for certain principal structural elements (PSEs) related to fuselage cutouts and to reduce an inspection threshold for an existing ALI task on the aft entry door. This AD results from data obtained from the manufacturer's fatigue testing. We are issuing this AD to detect and correct fatigue cracking of certain PSEs, which could result in reduced structural integrity of the airplane.
82-27-09: 82-27-09 EMBRAER: Amendment 39-4527. Applies to Model EMB-110, Serial Number 110001 and up, airplanes certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To prevent loss of the airplane's primary flight controls, within the next 100 hours time-in- service after the effective date of this AD on airplanes having more than 1000 hours time-in-service or prior to the accumulation of 1100 hours time-in-service on airplanes having less than 1000 hours time-in-service and within 1000 hours time-in-service thereafter, accomplish the following: a. Inspect the primary flight control cables in accordance with the instructions contained in EMBRAER Service Bulletin No. 110-27-064, dated September 28, 1982. 1) If cables are within the limits prescribed in Section II of "Maintenance Manual - Flight Controls," lubricate and rerig in accordance with EMBRAER Service Bulletin No. 110-27-064 and applicable Maintenance Manuals. 2) Ifcables are worn and/or have broken wires beyond the limits of Section II of "Maintenance Manual - Flight Controls," remove and replace cables in accordance with Section III of "Maintenance Manual - Flight Controls." b. The time-in-service between the repetitive inspections required herein may be adjusted up to plus 10 percent of any specified inspection interval required by this AD to facilitate accomplishing these inspections concurrent with other scheduled maintenance on the airplane. c. Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. d. An equivalent method of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, FAA, P.O. Box 20636, Atlanta, Georgia 30320. This amendment becomes effective on January 10, 1983.
87-10-11: 87-10-11 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-5976. Final copy of Telegraphic AD. Applies to the following helicopters certificated in any category (Airworthiness Docket No. 87-ASW-22). (a) Model 206A and 206B helicopters equipped with the following mast assemblies, P/N 206-010-332-121: Serial Numbers FAJF-58340 thru 58353, 58395 thru 58398, 58400, 58402 thru 58408, 58421 and 58423 thru 58434. NOTE: The following model 206B serial numbered helicopters were delivered with the affected masts: 3933, 3934, 3937 thru 3940, 3942, 3944 thru 3946, 3953 thru 3955, and 3958. (b) Model 206L, 206L-1, and 206L-3 helicopters equipped with the following mast assemblies, P/N 206-040-535-105: Serial Numbers NJF-935 thru 973, 1000, 1003, 1004, 1006 thru 1012, 1014 thru 1019, 1022 thru 1024, 1026, 1040 thru 1042, 1046, 1050 thru 1057, 1059, 1066, 1068, 1073, 1079, 1086, 1087, 1089 thru 1097, 1099, 1101, 1102, 1123, 1124, 1129, 1135, 1141, 1143, 1145, 1146, 1149, 1151, 1153, 1156, 1157, 1161, 1162, 1165, 1167, and 1169 thru 1172. NOTE: The following Model 206L-3 serial numbered helicopters were delivered with the affected masts: 51173 thru 51175, 51178, 51179, 51181, 51183 thru 51185, 51187 thru 51191, 51194 thru 51205, and 51208 thru 51211. Compliance is required as indicated, unless already accomplished. To prevent failure of the main rotor mast, accomplish the following: (a) Before further flight, determine if an affected serial number main rotor mast is installed on the helicopter. (b) Within the next 25 hours' time in service after receipt of this AD but no later than May 31, 1987, remove the affected serial number main rotor mast from service and replace it with an airworthy part. (c) An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be used when approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region, Fort Worth, Texas 76193-0170. NOTE: Bell Helicopter Alert Service Bulletin Nos. 206-87-37, dated 4/23/87 and 206-87-44, dated 4/23/87 pertain to this AD. This amendment becomes effective August 8, 1988, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD No. 87-10-11 issued May 19, 1987, which contained this amendment.
85-15-03: 85-15-03 AEROSPATIALE (SUD NORD): Amendment 39-5099. Applies to the Nord Model 262A series airplanes which have not incorporated STC SA2369SW, certificated in any category. Compliance required within 90 days after the effective date of this airworthiness directive (AD), unless already accomplished. To prevent undetected system failures or malfunctions in the windshield and turbine engine anti-icing systems, accomplish the following: A. Install additional fuses in the windshield anti-icing control circuitry for all windshield panels in accordance with Nord Service Bulletin No. 30-14, dated September 29, 1971 (which constitutes Nord modification No. 733), on Nord Model 262A series airplanes having serial numbers 8 through 20, 22 through 27, 29 through 35, 37 through 42, 47 through 50, 54, 56, 69, 74, and 84. B. Accomplish modifications to the turbine engine anti-icing control circuitry described in the planning section, paragraph I.C. of Nord Service Bulletin No. 30-15, dated October 29, 1971, as revised August 27, 1974 (which constitutes Nord modification No. 669). Accomplish the modifications in accordance with the Section II, Accomplishment Instructions, of the service bulletin on Nord Model 262A series airplanes having serial numbers 4 through 27, 29 through 35, 37 through 42, 47 through 50, 54, 56, 57, 69, and 84. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, Aircraft Certification Division, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective August 22, 1985.
2007-02-18: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 767-200, -300, and -300F series airplanes. That AD currently requires an inspection of visually accessible areas for indications of overheating of the heater tape attached to the potable water fill and drain lines in the forward and aft cargo compartments, exposed foam insulation or missing or damaged protective tape around the potable water fill and drain lines, and debris or contaminants on or near the potable water fill and drain lines. That AD also requires corrective action, as necessary. This new AD requires repetitive inspections of the forward and aft cargo compartments, as applicable, for discrepancies of the potable water supply and gray water drain lines; and applicable corrective actions if necessary. This AD also requires replacing the heater tapes on the potable water supply and gray water drain lines of the forward and aft cargo compartments, as applicable, withnew ribbon heaters, or deactivating and removing any defective heater tape and wrapping the drain line with foam insulation; either action ends the repetitive inspections. This AD results from a report of a fire in the aft cargo compartment. We are issuing this AD to prevent overheating of the heater tape on potable water fill and drain lines, which may ignite accumulated debris or contaminants on or near the potable water fill and drain lines, resulting in a fire in the airplane.
89-12-08: 89-12-08 ISRAEL AIRCRAFT INDUSTRIES (IAI): Amendment 39-6233. Applicability: Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks in the hinge lugs of the horizontal stabilizer aft spar splice fitting (hinge assembly), accomplish the following: A. Within the next 75 flight hours time-in-service after the effective date of this AD, unless previously accomplished within the last 225 flight hours time-in-service, conduct a visual inspection of the horizontal stabilizer aft spar splice fitting (hinge assembly), Part Number 453005-501, in accordance with the following IAI service bulletins entitled "Horizontal Stabilizer Aft Spar Splice Fitting P/N 453005-501 (Hinge Assembly) Inspection", as appropriate: Model Service Bulletin 1121, 1121A, 1121B 1121-55-003, Revision 1, dated August 8, 1988 1123 1123-55-006, Revision 1, datedAugust 8, 1988 1124, 1124A 1124-55-020, Revision 2, dated August 8, 1988 B. If no cracks are found, repeat the inspection required by paragraph A., above, at intervals not to exceed 300 hours time-in-service. C. If cracks are found, replace the splice fitting prior to further flight, in accordance with the following IAI service bulletins entitled "Horizontal Stabilizer Assembly - Inspection, Repair, and Improvement (AFC 2037)," as appropriate: Model Service Bulletin 1121, 1121A, 1121B 1121-55-004, Revision 2, dated October 21, 1988 1123 1123-55-007, Revision 2, dated October 21, 1988 1124, 1124A 1124-55-021, Revision 3, dated October 21, 1988 D. Following replacement of the splice fitting, described in the above service bulletins, repeat the inspection required by paragraph A. of this AD at intervals not to exceed 300 hours time-in-service. E. 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. F. 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 Israel Aircraft Industries, Delaware Office, P.O. Box 10086, Wilmington, Delaware 19850. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This AD supersedes AD 86-14-02, Amendment 39-5341, which became effective on August 4, 1986. This amendment (39-6233, AD 89-12-08) becomes effective on July 10, 1989.
2019-15-04: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report of a mis-installed no-back pawl discovered on a horizontal stabilizer trim actuator (HSTA). This AD requires an inspection to verify the horizontal stabilizer trim electronic control unit (HSTECU) part number, a software upgrade for certain HSTECUs, and installation of HSTECUs with upgraded software. The FAA is issuing this AD to address the unsafe condition on these products.
83-24-06: 83-24-06 CANADAIR: Amendment 39-4777. Applies to all Canadair Model CL-44D4 and CL-44J airplanes certificated in all categories. Compliance required as indicated unless previously accomplished. To ensure structural integrity of the upper main landing gear actuator eye attachment pins, accomplish the following within the next 100 hours time in service or 25 landings, whichever occurs first, after the effective date of this airworthiness directive (AD), unless accomplished within the last 1100 hours time in service or 275 landings, and thereafter at intervals not to exceed 1200 hours time in service or 300 landings, whichever occurs first. 1. Inspect both left and right upper main landing gear actuator eye attachment pins, P/N 44-87815, for cracks in accordance with paragraph 2.1 of Canadair Service Information Circular (SIC) No. 441-CL44, dated June 8, 1981. 2. Replace cracked parts with new or serviceable parts of the same part number prior to further flight. 3. Alternate means of compliance with the AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 4. Aircraft may be ferried to a base for maintenance in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations. 5. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of an operator, if the request contains substantiating data to justify the adjustment period. This amendment becomes effective December 20, 1983.
2000-24-22: This amendment adopts a new airworthiness directive (AD) that applies to all S.N. CENTRAIR Model 201B gliders. This AD requires you to modify the rear canopy emergency release system. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to prevent the rear canopy retaining strap from not releasing properly during the emergency egress procedure because of the current design of the rear canopy emergency release system. This condition, if not corrected, will not allow the rear canopy to completely separate from the glider and could result in potential injury to the pilot during an emergency egress.
84-18-07: 84-18-07 WALTER KIDDE AND OVERLAND AVIATION SERVICE CO: Amendment 39-4915. Applies to Walter Kidde discharge cartridges Part Number (P/N) 873571, 876296, 897776, and 898558 manufactured prior to July 1984, and Overland Aviation Service Co. discharge cartridges P/N OA873571, OA876296, and OA876299 manufactured prior to August 7, 1984. Compliance: Required within thirty (30) calendar days or at installation on any aircraft, whichever occurs later, unless already accomplished. To prevent hazards in flight associated with the non-operation of the fire extinguisher caused by non-firing of the discharge cartridge(s), accomplish the following: (a) Pull the applicable circuit breakers and disconnect the fire extinguisher bottle electrical plugs from the discharge cartridge. Inspect the electrical receptacle of the cartridge for compressed aluminum foil, which may have the appearance of solder and remove if present. Reinstall the plug and reset the applicable circuit breaker. (b) An equivalent means of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, 1075 Innerloop Road, College Park, Georgia 30337; telephone (404) 763-7248. This amendment becomes effective on September 21, 1984.
87-10-01: 87-10-01 PRATT & WHITNEY CANADA: Amendment 39-5959. Final copy of priority letter AD. Applies to Pratt & Whitney Canada (PWC) JT15D-1, -1A, -1B, -4, -4B, and -4D turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent failure of certain fan blades, accomplish the following within the next 15 calendar days or within the next 25 hours time in service from the effective date of this AD, whichever occurs first, and thereafter prior to the installation of any non-inspected fan blades: (a) Visually inspect the fan blade root fillet radius, including the area on the airfoil one-half inch above the radius runout, for surface finish in accordance with the accomplishment instructions of PWC Service Bulletin (SB) Number 7257, Revision Number 2, dated July 2, 1987. NOTE: Prior compliance with the accomplishment instructions of PWC SB Number 7257, dated April 23, 1987, is an equivalent means of compliance. (b) Remove from service, fan blades which exhibit machining striations and replace with a serviceable part, prior to further flight. (c) Aircraft may be ferried in accordance with the provisions 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 this 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 airworthiness inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance times specified in this AD. PWC SB Number 7257, Revision Number 2, dated July 2, 1987, identified and described in this document is incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive whohave not already received this document from the manufacturer may obtain copies upon request to Pratt & Whitney Canada, Box 10, Longueuil, Quebec, Canada J4K 4X9. This document may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 87-ANE-15, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-5959, becomes effective July 15, 1988, as to all persons except those persons to whom it was made immediately effective by priority letter AD Number 87-10-01, issued May 7, 1987, which contained this amendment.
2019-14-11: The FAA is adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Model DA 42 NG and Model DA 42 M-NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The unsafe condition in the MCAI is insufficient clearance of the gust lock mounts on the pilot side rudder pedals. The FAA is issuing this AD to address the unsafe condition on these products.
87-23-05 R1: 87-23-05 R1 PRATT & WHITNEY: Amendment 39-5755 as revised by Amendment 39-6296. Applicability: Pratt & Whitney (PW) JT9D-7R4D, -7R4D1, -7R4E, -7R4E1, -7R4E4, -7R4G2, and -7R4H1 series turbofan engines. Compliance: Required as indicated, unless already accomplished. To prevent fan blade fragment penetration of the fan case assembly, accomplish the following prior to December 31, 1990: (a) Modify and reidentify JT9D-7R4G2 series turbofan engines in accordance with PW Service Bulletin (SB) JT9-7R4-72-311, Revision 3, dated February 19, 1988, as follows: (1) Modify fan case assembly by installing shield, Part Number (P/N) 802094. (2) Modify outer front fan exit case assembly (fan exit case and vane assembly), by installing ring segments, P/N 803264-01, 803265-01, and 802448. (3) Reidentify the modified fan case assembly, outer front fan exit case assembly, and the fan exit case and vane assembly. (b) Modify and reidentify JT9D-7R4D, -7R4D1, -7R4E, -7R4E1, -7R4E4, and -7R4H1 series turbofan engines in accordance with PW SB JT9D-7R4-72-312, Revision 5, dated March 31, 1989, as follows: (1) Modify fan case assembly by installing shield, P/N 802095, on engines with steel fan case assemblies and shield, P/N 802096, on engines with titanium fan case assemblies. (2) Modify outer front fan exit case assembly, or detail of fan exit case and vane assembly, and install ring segments, P/N 803261-01, 803262-01, and 802447. (3) Reidentify the modified fan case assembly, the outer front fan exit case assembly, and the fan exit case and vane assembly. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) An alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety, submitted through an FAA Airworthiness Inspector, may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts 01803. The modification and reidentification of the fan case assembly, outer front fan exit case assembly, and the fan exit case and vane assembly shall be done in accordance with PW SB JT9D-7R4-72-311, Revision 3, dated February 19, 1988 [pages 1, 7, 9-12, 17, 21, and 24, Revision 3, dated February 19, 1988; pages 2-6, 8, 13-16, 18-20, 22, and 23, Revision 2, dated August 19, 1987]; or PW SB JT9D-7R4-72-312, Revision 5, dated March 31, 1989 [pages 1, 3, 7-18, Revision 5, dated March 31, 1989; page 2, Revision 2, dated June 26, 1987; page 4, Revision 5, dated February 9, 1987; and page 6, Original issue, dated January 19, 1987]. 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 Pratt & Whitney, Publications Department, P.O. Box 611, Middletown, Connecticut 06457. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, NW, Room 8301, Washington, DC 20591. This amendment (39-6296, AD 87-23-05 R1) becomes effective on March 23, 1990.
2019-15-05: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000-AE3, Trent 1000- CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000-P3, Trent 1000-Q3 and Trent 1000-R3 engines. This AD requires removal of the affected high-pressure turbine (HPT) disk front cover plate before reaching its new life limit. This AD was prompted by a recent analysis that determined the HPT disk front cover plate may have a safe life below its declared life limit. The FAA is issuing this AD to address the unsafe condition on these products.
95-25-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes. This action requires inspection(s) to detect cracks of the fuselage-mounted half of hinge assemblies of the small cargo door, and replacement of any cracked hinge assembly with a new hinge assembly. This amendment is prompted by a report that the hinges of the small cargo door on these airplanes are made of a material that is sensitive to stress corrosion cracking. The actions specified in this AD are intended to prevent failure of the hinges of the small cargo door due to stress corrosion cracking, which could result in opening and/or separation of the door while the airplane is in flight, and resultant rapid decompression and/or structural damage to the airplane.
2007-01-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires inspecting for fouling and chafing damage of the outboard brake control cable of the main landing gear, replacing the control cable if necessary, reworking the control cable cover, and, if applicable, manufacturing/installing an offset plate on the control cable cover. This AD results from a review of brake control cable operation conducted by the manufacturer. We are issuing this AD to prevent abrasion and wear of the outboard brake control cable, which could lead to cable separation and reduced control of airplane braking.
97-06-13: 97-06-13 ROLLS-ROYCE PLC: Amendment 39-9970. Docket 97-ANE-09. Applicability: Rolls-Royce plc (R-R) RB.211 Trent 800 series turbofan engines, installed on but not limited to Boeing 777 series aircraft. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent loss of oil, that could cause an engine fire, and inflight engine shutdowns and airplane diversions caused by oil loss and from bearing failures, accomplish the following: (a) Inspect angle drive upper shroud tubes as follows: (1) Within 50 CIS after the effective date of this AD, visually inspect and measure the frettage and fluorescent penetrant inspect (FPI) for cracks the angle drive upper shroud tubes in accordance with R-R Service SB No. RB.211-72-C089, Revision 1, dated January 24, 1997. (2) Thereafter, at intervals not to exceed 50 CIS since last inspection, visually inspect and measure the frettage and FPI for cracks the angled drive upper shroud tubes, in accordance with R-R SB No. RB.211-72-C089, Revision 1, dated January 24, 1997. (3) Prior to further flight, remove from service angled drive upper shroud tubes that exhibit frettage measured in excess of 0.020 inches, or any cracks, and replace with serviceable parts. (4) Installation of an improved angled drive upper shroud tube with a lower splitter fairing with revised sealing in accordance with R-R SB No. RB.211-72-C114, dated February 6, 1997, constitutes terminating action to the inspection requirements of paragraphs (a)(1), (a)(2), and (a)(3) of this AD. (5) Prior to initiation of ETOPS, or prior to September 30, 1997, whichever occurs first, install an improved angled drive upper shroud tube with a lower splitter fairing with revised sealing in accordance with R-R SB No. RB.211-72-C114, dated February 6, 1997. (b) Inspect the intermediate gearbox housing (IGH) and external gearbox lower bevel box (LBB) housing as follows: (1) Within 5 CIS after the effective date of this AD, perform an initial visual inspection of the IGH and LBB housing for cracks, in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (2) Within 10 CIS after the effective date of this AD, perform an initial FPI of the IGH for cracks, in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (3) Thereafter, at intervals not to exceed 5 CIS since last visual inspection, visually inspect the IGH and LBB housing for cracks, and at intervals not to exceed 10 CIS since last FPI, FPI the IGH, in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (4) Within 10 CIS after the effective date of this AD, perform an FPI of the IGH for porosity in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (5) Within the next 5 CIS, remove from service IGHs that exhibit porosity levels in excess of the acceptable criteria listed in the SB and replace with serviceable parts. (6) Prior to further flight, remove from service cracked IGHs and LLB housings and replace with serviceable parts. (c) Inspect the master magnetic chip detector as follows: (1) Within 100 hours time in service (TIS) after the effective date of this AD, perform an initial inspection of the master magnetic chip detector in accordance with Mandatory SB No. RB.211-79-C093, Revision 1, February 28, 1997. (2) Thereafter, at intervals not less than 60 hours TIS and not greater than 130 hours TIS since last inspection, perform repetitive inspections of the master magnetic chip detector in accordance with Mandatory SB No. RB.211-79-C093, Revision 1, dated February 28, 1997. (d) 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. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the EngineCertification Office. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the inspection requirements of this AD can be accomplished. (f) The actions required by this AD shall be performed in accordance with the following R-R service documents: Document No. Pages Revision Date SB No. RB.211- 72-C089 1-3 1 January 24, 1997 Total pages: 3. SB No. RB.211- 72-C129 1-3 2 March 21, 1997 4-6 1 March 7, 1997 7 2 March 21, 1997 Total pages: 7. SB No. RB.211- 72-C114 1-48 Original February 6, 1997 Supplement 1-4 Original February 6, 1997 Total pages: 52. SB No. RB.211- 79-C093 1,2 1 February 28, 1997 Total pages: 2. 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 Rolls-Royce North America, Inc., 2001 South Tibbs Ave., Indianapolis, IN 46241; telephone (317) 230-3995, fax (317) 230-4743. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on May 15, 1997.