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73-18-03: 73-18-03 ROCKWELL INTERNATIONAL: Amendment 39-1707 as amended by Amendment 39-3201. Applies to Model NA-265-40 Serial Numbers 282-1 and subsequent; Model NA-265-50 Serial Number 287-1; Model NA-265-60 Serial Numbers 306-1 through -139; Model NA-265-70 Serial Numbers 370-1 through -9; and Model NA-265-80 Serial Numbers 380-1 through -61. Compliance required as indicated after the effective date of this AD. To detect possible cracks, corrosion, or breaks in the surface finish in the wing spars and related areas, accomplish the following: (a) On or before June 18, 1974, unless previously accomplished within one year, and at intervals not to exceed two years thereafter, inspect the upper and lower flanges of the front and rear spars in the area of the wing center section, and the lugs on the rear spar and wing trailing edge panel rib, per the instructions of Rockwell International, Inc., Sabreliner Division Service Bulletin No. 73-11, dated June 18, 1973, or later FAA-approved revisions, or an equivalent inspection approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) Prior to further flight, if cracks, corrosion, or breaks in the surface finish are found in the front or rear spars in the area of the wing center section, replace with like serviceable parts, or repair in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) Prior to further flight, if cracks are found in the lugs on the rear spar and wing trailing edge rib, replace with like serviceable parts, or repair in a manner approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) Airplanes may be operated in accordance with FAR 21.197 to a base where maintenance is to be performed. Amendment 39-1707 became effective October 8, 1973. This Amendment 39-3201 becomes effective May 5, 1978.
2006-10-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-223, -321, -322, and -323 airplanes. This AD requires repetitive inspections of the firewall of the lower aft pylon fairing (LAPF), and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports of cracking of the LAPF firewall. We are issuing this AD to detect and correct this cracking, which could reduce the effectiveness of the firewall and result in an uncontrolled engine fire.
87-25-02: 87-25-02 SIKORSKY AIRCRAFT: Amendment 39-5778. Applies to all Model S-76A and S-76B series helicopters through and including serial number 760350, certified in any category. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible loss of AC electrical power due to 26 VAC transformer single ground connection failure, provide separate ground connections for 26 VAC transformers 1 and 2. NOTE: Sikorsky Service Bulletin No. 76-24-5, AC Electrical Power System - AC Power Transformer Ground Wires Termination-Separation of, dated October 19, 1987, constitutes an acceptable means of compliance with this requirement. This amendment becomes effective December 31, 1987.
89-02-03: 89-02-03 BEECH: Amendment 39-6104. Applicability: Model 200 (Serial Numbers BB-2 through BB-161) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished per Beech Service Bulletin No. 2240, dated February 1988, or Beech Letter No. 52-83-0030, dated January 20, 1983, or Beech Letter No. 52-85-0049, dated April 17, 1985. To prevent possible failure of the wing main outboard spar, accomplish the following: (a) Within the next 200 hours time-in-service (TIS) after the effective date of this AD, or upon accumulating 10,000 hours TIS, whichever occurs later, replace both wing main outboard spars in accordance with Beech Service Bulletin No. 2240, dated February 1988. Only the left wing main spar need be replaced for Serial Nos. BB-149 through BB-161. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalentmeans of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Department 52, Wichita, Kansas 67201-0085; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6104, AD 89-02-03) becomes effective on February 8, 1989.
2019-05-13: We are removing AD 2007-22-05 and AD 2013-13-13 (referred to after this as ``the affected ADs''), which applied to Airbus SAS Model A300-600 and A310 series airplanes. The affected [[Page 10406]] ADs required certain actions to address various unsafe conditions. The affected ADs are no longer necessary because we have since issued other ADs to address these unsafe conditions. Accordingly, we are removing the affected ADs.
85-01-04: 85-01-04 PITTS: Amendment 39-4980. Applies to Model S-2A (S/N's 2001 through 2105) airplanes certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent loss of normal aileron and elevator control: (a) Visually inspect the cockpit control tube assembly using a 10 power glass for cracks in the area of the welds attaching the P/N 2-5100-12 stick housings to the P/N 2-5100-11 tube. (1) If cracks are detected weld shut the cracks and install a P/N 2-5100-20 gusset at both the fore and aft stick housing locations in accordance with Pitts Service Letter No. 5, Revision B. (2) If cracks are not present, install P/N 2-5100-20 gussets in accordance with Pitts Service Letter No. 5, Revision B. (b) The aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) Installation of P/N 2-5100-19 gussets in accordance with Pitts Service Letter No. 5, Revision A, satisfies the requirements of this AD. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Denver Aircraft Certification Office, Federal Aviation Administration, Northwest Mountain Region, 10455 East 25th Avenue, Suite 307, Aurora, Colorado 80010; Telephone (303) 340-5594. This amendment becomes effective on January 21, 1985.
99-03-10: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-03-10 which was sent previously to all known U.S. owners and operators of Agusta Model A109E helicopters by individual letters. This AD requires, before further flight, inspections of the exhaust ejector locking system, clamp, and dampers for each engine. This AD also requires, at specified time intervals, verifying the torque of the metallic clamps and installing safety wire on the metallic clamps; inspecting and modifying the ejector saddles and the locking metallic clamps; and inspecting the metallic clamps, locking mechanisms, and dampers. This amendment is prompted by an inflight incident in which a metallic clamp which secured the left-hand engine exhaust ejector to the ejector saddle became detached and subsequently separated from the helicopter. The actions specified by this AD are intended to prevent loss of the metallic clamp or the engine exhaust ejector, which could result in damage to the main or tail rotor system and subsequent loss of control of the helicopter.
2006-10-08: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 767-200, -300, and -300F series airplanes. That AD currently requires repetitive inspections of the lubrication passage and link assembly joint in the inboard and outboard flaps of the trailing edge for discrepancies, and corrective action if necessary. This new AD requires new inspections for cracking or severe wear of the bearings of the link assembly, inspections of any link assembly not previously inspected for damage, and corrective actions if necessary. This AD also ends the existing repetitive inspections for certain airplanes, and extends the repetitive interval for the existing repetitive inspections and the compliance time for the corrective action on certain other airplanes. This AD also provides an optional terminating action. This AD results from additional reports indicating fractured bearings of the link assembly joint in the inboard and outboard flaps of the trailing edge. We are issuing this AD to prevent failure of the bearings in the link assembly joint, which could result in separation of the inboard or outboard flap and consequent loss of control of the airplane. \n\nDATES: This AD becomes effective June 19, 2006. \n\n\tThe Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of June 19, 2006. \n\n\tOn February 14, 2002 (67 FR 4328, January 30, 2002), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 767-27A0167, dated December 7, 2000.
2019-05-07: We are superseding Airworthiness Directive (AD) 2017-20-01 for certain Honeywell International Inc. (Honeywell) TFE731-20 and TFE731- 40 turbofan engines. AD 2017-20-01 required removing the affected fan disk and replacing it with a fan disk eligible for installation. Since we issued AD 2017-20-01, we determined that some turbofan engine models were omitted from the applicability of AD 2017-20-01. This AD adds turbofan engine models to the applicability and removes the Honeywell TFE731-20 turbofan engine model from the applicability. This AD requires removal of affected fan disks and replacement with parts eligible for installation. This AD was prompted by two fan disks found with surface rollovers in the dovetail slot area. We are issuing this AD to address the unsafe condition on these products.
87-05-08: 87-05-08 MCDONNELL DOUGLAS: Amendment 39-5559. Applies to McDonnell Douglas Model DC-9-81, -82, and -83 series airplanes, certificated in any category, equipped with Air Cruiser Company emergency exit evacuation slide part numbers D29984-103 and -109 having serial numbers prior to 0093. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent jamming during deployment of the emergency evacuation slide, accomplish the following: \n\n\tA.\tWithin 6 months after the effective date of this AD, modify the emergency evacuation slide deployment strap clip in accordance with Air Cruiser Service Bulletin 304-25-3, dated January 21, 1986, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles 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 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 Air Cruisers Company, P.O. Box 180, Belmar, New Jersey 07719-0180. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective March 25, 1987.
2006-14-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-200 and A330-300 series airplanes; and Airbus Model A340-200 and A340-300 series airplanes. This AD requires lubrication of the upper and lower shortening mechanism (SM) link of the main landing gear, and consequent detection of resistance or blockage of the greaseway. Depending upon the resistance finding and upon whether or not the airplane has a certain modification, this AD also requires various other actions including unblocking the greaseway; accomplishing all necessary repairs; performing various inspections; and accomplishing the eventual replacement of the SM8 pin, if necessary. This action is necessary to prevent failure of the landing gear lengthening system, which could result in reduced controllability of the airplane on the ground during landing. This action is intended to address the identified unsafe condition.
2006-05-01: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 500, 700, and 800 series turbofan engines. This AD requires inspecting all engines to determine those that are equipped with a suspect oil filler cap assembly. This AD also requires, within seven days of the effective date of this AD, an initial and repetitive check of oil cap security following oil servicing of multiple-engine airplanes having more than one suspect oil filler cap assembly installed. Finally, this AD requires replacing affected oil filler cap assemblies. This AD results from four in- service oil loss events since March 2005, following failures to properly install the oil tank filler cap after oil servicing. We are issuing this AD to prevent oil loss that could result in multiple engine in-flight shutdowns during a flight.
2019-05-09: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-251N and -271N airplanes, and Model A321-253N airplanes. This AD was prompted by reports of low clearance between the electrical harness and nearby hydraulic pipes in the inboard trailing edge of the wing. This AD requires repetitive detailed inspections of certain electrical harnesses for discrepancies and corrective actions, if necessary, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. We are issuing this AD to address the unsafe condition on these products.
2019-05-04: We are adopting a new airworthiness directive (AD) for MDHI Model 369A, 369D, 369E, 369FF, 369H, 369HE, 369HM, 369HS, 500N, and 600N helicopters. This AD requires inspecting each main rotor blade (MRB) for a crack. This AD was prompted by reports of cracked MRBs. The actions of this AD are intended to address an unsafe condition on these helicopters.
92-22-15: 92-22-15 PRATT & WHITNEY CANADA: Priority Letter issued on October 21, 1992. Docket No. 92- ANE-48. Applicability: Pratt & Whitney Canada (PWC) JT15D-5A turbofan engines installed on but not limited to Cessna Model 560 (Citation V) aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent high temperature deterioration of the flow divider start valve diaphragm that can result in uncommanded engine shutdowns with the inability to restart the engine, accomplish the following: (a) Modify flow divider start valve PWC Part Number 3038429 in accordance with the Accomplishment Instructions of PWC Service Bulletin No. 7371, dated October 14, 1992, before accumulating more than 50 hours time in service after receipt of this Priority Letter AD, or prior to December 1, 1992, 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 theManager, Engine Certification Office. The request should be forwarded through an appropriate FAA 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 aircraft to a location where the requirements of this AD can be accomplished. (d) Copies of the applicable service information may be obtained from Pratt & Whitney Canada, 1000 Marie-Victorin, Longueuil, Quebec, Canada J4G 1A1. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts. (e) Priority Letter AD 92-22-15, issued October 21, 1992, becomes effective upon receipt.
89-07-07 R1: 89-07-07 R1 GARRETT ENGINE DIVISION, ALLIED-SIGNAL, INC. (formerly Garrett Turbine Engine Co., GTEC, formerly AIResearch Manufacturing Company of Arizona): Amendment 39-6140 as revised by Amendment 39-6336. Applicability: Garrett Models TPE331-25AA, -25AB, -25DA, -25DB, -25FA, -43A, -43BL, -47A, -55B, - 61A, -1, -2, -2UA, -U, -3UW, -5, -6, -6A, -8, -10, -10R, -10U, 3-10UA, -10UF, -10UG, -10UGR, -10UR, -11U turboprop and TSE331-3U turboshaft engines. Compliance: Required as indicated, unless already accomplished. Engines previously in compliance with AD 86-12-02 in accordance with Garrett Service Bulletin (SB) TPE331-72-0533, dated May 9, 1986, or SB TPE331-72-0533, Rev. 1, dated November 26, 1986, are in compliance with this AD. To prevent turbine failure, accomplish the following: (a) Inspect and modify applicable engines in accordance with the Accomplishment Instructions of Garrett (SB) TPE331-72-0533, Revision 2, dated March 11, 1988, previously incorporated by reference in AD 89-07-07, on March 20, 1989. This work shall be performed at first access to the oil scavenge pump assembly, or within 1,800 operating hours after April 9, 1989, or within 18 months after April 9, 1989, whichever occurs first. (b) 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. (c) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 3229 East Spring Street, Long Beach, California 90806- 2425, may approve an equivalent means of compliance or an adjustment of the compliance schedule which provides an equivalent level of safety. Copies of Garrett SB TPE331-72-0533, Revision 2, dated March 11, 1988, previously incorporated by reference in AD 89-07-07 on March 20, 1989,may be obtained upon request from Garrett General Aviation Services Division, Distribution Center, 2340 East University, Phoenix, Arizona 85034. Copies may be inspected at the 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, Room 8301, Washington, DC 20591. Amendment 39-6140, AD 89-07-07, superseded AD 86-12-02 (Amendment 39-5371) which was effective on September 5, 1986, as to all persons except those to whom it was made immediately effective by Priority Letter AD 86-12-02 which was issued on June 5, 1986. This AD revises Amendment 39-6140 (54 FR 11368; March 20, 1989), AD 89-07-07, which became effective on April 9, 1989.
88-07-06: 88-07-06 ALLISON GAS TURBINE DIVISION, GENERAL MOTORS CORPORATION (Allison, formerly Detroit Diesel Allison): Amendment 39-5860. Applies to Allison Model 250-C30 Series engines installed in, but not limited to, Sikorsky Model S-76A, Bell Model 206L-3, Bell Model 206L-1, modified to incorporate the Allison 250-C30 engine, Aerospatiale Model AS-350D "ASTAR" modified to incorporate the Allison 250-30M engine, and McDonnell Douglas Helicopter Company (Hughes) Model 369F and 369FF aircraft. The following engine models and turbine serial numbers are affected: ENGINE MODEL TURBINE SERIAL NUMBER 250-C30 CAT 90001 thru 90683, 95001 thru 95600 250-C30S CAT 90001 thru 90683, 95001 thru 95600 250-C30M CAT 95001 thru 95600 250-C30P CAT 95001 thru 95600, 97501 thru 97550 250-C30L CAT 95001 thru 95600, 97501 thru 97550 250-C30R(T703-AD-700) AT 19001 thru 19140 EXCEPT: Existing model 250-C30 series engines which have incorporated Part II or III of Allison CommercialEngine Alert Bulletin 250-C30, CEB-A-72-3165, dated August 31, 1987, or FAA approved equivalent. Compliance is required as indicated, unless already accomplished. To prevent possible cracks of the Gas Producer Support Pressure Oil Tube Assembly, P/N 6892825, or P/N 23037410, from progressing to where a loss of engine oil could cause an in-flight shutdown, accomplish the following: (a) Following the last flight of each day after the effective date of this AD, until compliance with paragraph (b) or (c) is accomplished, check for oil leaks and, if a leak is found remove before further flight the Gas Producer Support Pressure Oil Tube Assembly, P/N 23037410 or P/N 6892825, in accordance with Part I of Allison Commercial Engine Alert Bulletin 250-C30, CEB-A-72-3165, dated August 31, 1987, or FAA approved equivalent. NOTE: The checks required above may be performed by the pilot and must be recorded in accordance with FAR Section 43.9. (b) Replace Gas Producer Support Pressure Oil Tube Assembly P/N 23037410 with P/N 23038235 or an FAA approved equivalent in accordance with Part II of Allison Commercial Engine Alert Bulletin 250-C30, CEB-A-72-3165, dated August 31, 1987, not later than April 15, 1988. (c) Replace Gas Producer Support Pressure Oil Tube Assembly P/N 6892825 with number 8 Bearing Pressure Oil Fitting Assembly, P/N 23035275, and Tube Assembly, P/N 23038235, or FAA approved equivalents in accordance with Part III of Allison Commercial Engine Alert Bulletin 250-C30, CEB-A-72-3165, dated August 31, 1987, or FAA approved equivalent, not later than July 1, 1988. (d) Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FAR) 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018. (f) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Chicago Aircraft Certification Office may adjust the compliance time specified in this AD. Allison Commercial Engine Alert Bulletin 250-C30 CEB-A-72-3165 dated August 31, 1987, identified and described in this document, is 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 this document from the manufacturer may obtain a copy upon request to Allison Gas Turbine Division, General Motors Corp., P.O. Box 420, Indianapolis, Indiana 46206-0420. This document also may be examined at the office of Regional Counsel, Federal Aviation Administration, Attn: Rules Docket No. 87-ANE-26, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment becomes effective March 30, 1988.
98-18-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Schempp-Hirth K.G. (Schemmp-Hirth) Model Cirrus sailplanes. This AD requires modifying or replacing the connecting rod between the airbrake bellcranks, and replacing the existing 6 millimeter (mm) bolt with an 8 mm bolt. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the threaded bolt that is welded to the connecting rod between the airbrake bellcranks from breaking, which could result in loss of airbrake control with a possible reduction/loss of sailplane control.
2019-05-06: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD requires replacing the retaining ring and inspecting the hoist cable hook assembly (hook). This AD was prompted by a report that a hook detached from the hoist cable. The actions of this AD are intended to address an unsafe condition on these products.
96-25-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires inspections to detect chafing of the wire looms (bundles) in the wing and the horizontal stabilizer; and repair or replacement, protection, and realignment, if necessary. This amendment requires that those actions also be accomplished in certain areas of the main landing gear (MLG) bays. This amendment also requires installation of protective sleeves around the wire bundles, and realignment of bundles that are not guided centrally into the conduit end fittings, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report that electrical short circuiting could occur in the wire bundles in the MLG bays. The actions specified by this AD are intended to prevent such electrical short circuiting due to chafing of the wire bundles in the wing, horizontal stabilizer, or MLG bays.
86-23-08: 86-23-08 SIKORSKY AIRCRAFT: Amendment 39-5590. Applies to Model S-61 series helicopters, certificated in any category, with main rotor hub lower plate, P/N S6110-23009-6 or -8, installed. For helicopters with main rotor hub lower plates with more than 27,000 hours' time in service on the effective date of this AD, compliance is required prior to further flight, unless already accomplished, and thereafter at intervals not to exceed 27,000 hours' time in service. For helicopters with main rotor hub lower plate with 27,000 or less hours' time in service on the effective date of this AD, compliance is required prior to the accumulation of 27,000 hours' time in service, unless already accomplished, and thereafter at intervals not to exceed 27,000 hours' time in service. To prevent cracking of the main rotor hub lower plate, accomplish the following: (a) Remove and replace the main rotor hub lower plate, P/N S6110-23009-6 or -8, with a new or an airworthy part of the same part number that has less than 27,000 -hours' time in service. (b) In accordance with FAR sections 21.197 and 21.199, the helicopter may be flown to a base where compliance may be accomplished. (c) An alternate method of compliance or adjustment of the initial compliance time which provides an equivalent level of safety, may be approved by the Manager, 30 Sikorsky Boston Aircraft Certification Office, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective April 21, 1987, to all persons except those persons to whom it was made immediately effective by priority letter AD 86-23-08, issued November 17, 1986, which contained this amendment.
88-06-02: 88-06-02 CESSNA: Amendment 39-5900. Applicable to Model 550 series airplanes, serial numbers (S/N) 550-0561, -0562, -0564, -0565, -0566, -0568, and -0569; and Model S550 series airplanes, S/N S550-0140 through -0146, -0148, and -0149; certificated in any category. Compliance is required as indicated, unless previously accomplished. To preclude wiring failure, which could result in smoke and/or fire in the cabin, accomplish the following: A. For Cessna Model 550 series airplanes: Prior to next activation of the airplane's electrical power, disconnect the electrical power to the indirect lighting system, in accordance with Cessna Alert Service Letter SLA550-33-02, dated March 14, 1988. Electrical power may be reconnected to the indirect lighting system following replacement of the affected wiring harness described in, and in accordance with, Cessna Service Bulletin SB550-33-9, dated March 17, 1988, or later FAA-approved revisions. B. For Cessna Model S550 series airplanes: Prior to next activation of the airplane's electrical power, disconnect the electrical power to the indirect lighting system, in accordance with Cessna Alert Service Letter SLAS550-33-01, dated March 14, 1988. Electrical power may be reconnected to the indirect lighting system following replacement of the affected wiring harness described in, and in accordance with, Cessna Service Bulletin, SBS550-33-5, dated March 17, 1988, or later FAA-approved revisions. C. An alternate means of compliance which provides an acceptable level of safety may be used when approved by the Manager, Wichita Aircraft Certification Office, FAA, Central Region. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer, may obtain copies upon request to Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle,Washington, or the FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas. This amendment 39-5900 becomes effective May 10, 1988. It was effective earlier to all recipients of Priority Letter AD 88-06-02, issued March 16, 1988.
99-23-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires repetitive detailed visual inspections to detect cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing; and corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. 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 detect and correct fatigue cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing, which could result in reduced structural integrity of the belly fairing.
2019-05-05: We are superseding Airworthiness Directive (AD) 97-26-03 for Eurocopter Deutschland GmbH Model MBB-BK 117 A-1, MBB-BK 117 A-3, MBB- BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. AD 97-26-03 required visual inspections for cracks in the ribbed area of the main rotor (M/R) mast flange (flange). Since we issued AD 97-26-03, we have determined that a certain reinforced M/R mast is not affected by the unsafe condition. This new AD retains the requirements of AD 97-26-03 and removes a certain M/R mast from the applicability. The actions of this AD are intended to address an unsafe condition on these products.
98-01-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires repetitive operational tests of the override mechanism of the trimmable horizontal stabilizer (THS) to determine if the system functions correctly; and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent uncommanded movement of the THS, which could result in reduced controllability of the airplane.