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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.