Results
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.
87-16-09: 87-16-09 SHORT BROTHERS PLC: Amendment 39-5698. Applies to Model SD3-60, serial numbers SH3601 through SH3679, certificated in any category. Compliance required within 90 days after the effective date of this AD, unless previously accomplished. To prevent the potential for the loss of recorded information from the flight data recorder, due to corrosion, accomplish the following: A. Install a flight data recorder cover in accordance with the Shorts Service Bulletin No. SD360-31-04, Revision No. 2, dated October 1986. B. Inspect the installed flight data recorder for corrosion of the circuit cards and correct as required in accordance with the appropriate recorder maintenance manual. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordancewith FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Shorts Aircraft, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. This document 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. This amendment becomes effective September 10, 1987.
89-19-09: 89-19-09 FOKKER: Amendment 39-6323. (Docket No. 89-NM-95-AD) Applicability: Model F-27 series airplanes, Serial Number 10202, 10105 through 10684, 10686, 10687, and 10689 through 10692, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural capability of the fuselage and subsequent decompression of the airplane, accomplish the following: A. For airplanes in post-Service Bulletin F27/21-30 configuration, within 30 days after the effective date of this AD or upon the accumulation of 30,000 landings, whichever occurs later, inspect the external skin at the riveted connections between fuselage Station 1400 and the partial pressure bulkhead, in accordance with Fokker Service Bulletin F27/53-108, dated February 3, 1989. If cracks are found, repair prior to further flight, in accordance with the service bulletin. B. For airplanes in pre-Service Bulletin F27/21-30 configuration, within 30 days after the effective date of this AD, or upon the accumulation of 50,000 landings, whichever occurs later, inspect the external skin at the riveted connections between Fuselage Station 1400 and the partial pressure bulkhead in accordance with Fokker Service Bulletin F27/53-108 dated February 3, 1989. If cracks are found, repair prior to further flight, in accordance with the service bulletin. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, C-68966, Seattle, Washington 98168. This amendment (39-6323, AD 89-19-09) becomes effective on October 14, 1989.
98-25-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T98-25-51 that was sent previously to all known U.S. owners and operators of certain Airbus Model A310 and A300-600 airplanes by individual telegrams. This AD requires deactivation of both thrust reversers and a revision of the Airplane Flight Manual (AFM) to ensure that safe and appropriate performance is achieved during certain takeoff conditions. This action 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 inflight deployment of a thrust reverser, which could result in reduced controllability of the airplane.
86-20-06: 86-20-06 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5427. Applies to Bell Helicopter Textron, Inc., Model 214ST helicopters, S/N's 28101 through 28159, and Models 214B and 214B-1, S/N's 28001 through 28070, certificated in any category, equipped with main rotor drag brace assembly P/N 214-010-113-001. Compliance is required as indicated, unless already accomplished. (a) To prevent failure of the M/R drag brace assembly, P/N 214-010-113-001, on the Model 214ST helicopter, replace it with M/R drag' brace assembly, P/N 214-010-113-105, within the next 50 hours' time in service or within 30 days after the effective date of this AD, whichever comes first. (b) To prevent failure of the M/R drag brace assembly, P/N 214-010-113-001 on the Model 214B and 214B-1 helicopters, replace it with M/R drag brace assembly, P/N 214-010-113- 107, within the next 50 hours' time in service or within 30 days after the effective date of this AD, whichever comes first. (c) An alternate method of compliance which provides an equivalent level of safety with this AD may be used when approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment becomes effective October 18, 1986.
98-13-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires accomplishing a leakage check of all lavatory water tube/hose connections, and correcting the installation of these connections if leakage is found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent water leakage from the lavatory water duct system, which could collect in the fuselage, freeze in cold weather conditions, and cause the rudder control system to jam.
89-17-05: 89-17-05 BELL HELICOPTER TEXTRON, INC.: Amendment 39-6276. Applicability: Model 222, 222B, and 222U helicopters, certificated in any category, with horizontal stabilizer assembly, Part Number (P/N) 222-035-250-101, -103, or -105, installed. (Docket No. 89-ASW-16) Compliance: Required within the next 50 hours' time in service for horizontal stabilizer assemblies with more than 2,100 hours' time in service; compliance for horizontal stabilizers with less than 2,100 hours' time in service is required prior to the accumulation of 2,150 hours' time in service; and both thereafter at intervals not to exceed 300 hours' time in service. To prevent failure of the horizontal stabilizer assembly, which could result in loss of the helicopter, accomplish the following: (a) Perform the Part "A" of the "Accomplishment Instructions" of BHTI Alert Service Bulletin (ASB) No. 222-89-53, dated March 20, 1989, for the Model 222 and 222B; or ASB No. 222U-89-27, dated March 20,1989, for the Model 222U. (b) If a crack is detected, remove and replace with a serviceable horizontal stabilizer assembly prior to further flight. (c) The requirements of this AD do not apply if horizontal stabilizer assembly P/N 222-035-250-107 is installed for the Model 222 or P/N 222-035-250-109 is installed for the Models 222B and 222U. (d) An alternate method of compliance which provides an equivalent level of safety, may be approved by the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170. The inspection procedures shall be done in accordance with Part "A" of the "Accomplishment Instructions" of BHTI Alert Service Bulletin (ASB) No. 222-89-53, dated March 20, 1989, for the Model 222 and 222B; or ASB No. 222U-89-27, dated March 20, 1989, for the Model 222U. This incorporation by reference of ASB No 222-89-53 and ASB No. 222U-89-27, both dated March 20, 1989, 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the Office of the Assistant Chief Counsel, Southwest Region, 4400 Blue Mound Road, Room 158, Building 3B, Fort Worth, Texas, between 8 a.m. and 4 p.m. weekdays, except Federal holidays, or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, D.C. This amendment (39-6276, AD 89-17-05) becomes effective on August 28, 1989.
2019-05-08: We are superseding Airworthiness Directive (AD) 2015-12-08, which applied to all Airbus SAS Model A318 and A319 series airplanes and all Model A320-211, A320-212, A320-214, A320-231, A320-232, A320- 233, A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321- 231, and A321-232 airplanes. AD 2015-12-08 required an inspection to determine the batch number or installation date of the oxygen pipe assembly that is installed at the end of the right-hand crew distribution line, and replacement of the pipe if necessary. This AD revises the applicability to include additional airplane models and additional pipes to be replaced if necessary. This AD was prompted by further investigation that determined that affected oxygen pipes may have been installed on more airplanes than initially identified. We are issuing this AD to address the unsafe condition on these products.
99-22-15: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires repetitive inspections of the left and right roll spoiler actuators to check for signs of leakage and deformation of the housing, repetitive inspections of the gap between the left roll spoiler actuator housing cap and the actuator housing, repetitive torque checks of the left roll spoiler actuator housing cap attachment screws, and corrective action, if necessary. 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 oil leakage from the roll spoiler actuators, which could result in incorrect roll spoiler operation and reduced controllability of the airplane.
68-17-03: 68-17-03 PILATUS: Amendment 39-634. Applies to all Model PC-6 Series Airplanes. Compliance required as indicated. To detect cracks in the rudder end rib, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this Airworthiness Directive and thereafter at intervals not to exceed 50 hours time in service from the last inspection, inspect the rudder end rib P/N 6302.27 for cracks with the aid of a mirror. (b) If cracks are detected during any inspection prescribed in paragraph (a), replace the rudder end rib before further flight with a modified rudder end rib, P/N 6302.26 Pos. 2; channel reinforcement, P/N 113.40.06.002, and torque tube, P/N 113/40.06.003, in accordance with Pilatus Service Bulletin No. 80, dated April, 1968, or later Swiss Federal Air Office approved Revision or FAA approved equivalent. (c) The repetitive inspections required by paragraph (a) may be discontinued after the modified rudder end rib has been installed. This amendment becomes effective August 19, 1968.
86-07-09 R1: 86-07-09 R1 BOEING: Amendment 39-5280 as amended by Amendment 39-5309. Applies to all Boeing Model 757 and 767 airplanes, certificated in any category. To ensure the integrity of the cargo compartment smoke detection system, accomplish the following within 30 days after the effective date of this AD, unless already accomplished: \n\n\tA.\tReplace the lamps in the four Autronics Corporation Model 2156-204 cargo compartment smoke detectors and install placards in accordance with Autronics Service Bulletin 2156204-26-01, dated April 14, 1986, or later FAA-approved revision. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\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 inspections and/or modifications required by this AD. \n\n\tAll persons affected by this AD who have not already received the above specified service bulletin from the manufacturer may obtain copies upon request from the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. The service bulletin 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\tAmendment 39-5280 became effective April 22, 1986. \n\tThis Amendment 39-5309 becomes effective May 20, 1986.
85-16-06: 85-16-06 MCDONNELL DOUGLAS AND AIRBUS INDUSTRIE: Amendment 39-5112. Applies to McDonnell Douglas Model DC-10-15, -30, and KC-10A (Military) series airplanes, and CF6-50C powered Airbus Industrie Model A-300 series airplanes. Compliance is required as indicated.\n\n\tTo prevent failure of the fuel flowmeter tube assembly, accomplish the following, unless already accomplished:\n\n\tA.\tWithin the next 1000 flight hours after the effective date of this AD, inspect the fuel flowmeter tube assemblies in accordance with McDonnell Douglas Alert Service Bulletin A73-20, dated January 7, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region; or Airbus Industrie Service Bulletin A300-73-007 (associated with modification 5912), as appropriate. Perform the inspection every 1000 flight hours until paragraph B., below, is accomplished. If any cracks are found, accomplish the requirements of paragraph B. before any further revenue flight.\n\n\tB.\tWithin one year after the effective date of this AD, install the fuel flowmeter tube assembly P/N-ASLO538-503 in accordance with McDonnell Douglas DC-10 Alert Service Bulletin A73-20, dated January 7, 1985, or later revisions 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\tD.\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\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750(54-60). These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California.\n\n\tThis amendment becomes effective September 6, 1985.