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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.
2009-04-03: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) AE 3007A1E and AE 1107C turbofan/ turboshaft engines. This AD requires removal from service of certain 2nd stage, 3rd stage, and 4th stage compressor wheels, compressor cone shaft assemblies, and 1st to 2nd-stage turbine spacers at new, reduced, published life limits. This AD results from RRC applying an updated lifing methodology to the affected parts. We are issuing this AD to prevent low-cycle-fatigue failure of the parts listed in Table 1 of this AD, which could result in an uncontained engine failure and damage to the aircraft.
98-17-12: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4100 series airplanes, that requires an eddy current conductivity test to measure the conductivity of the upper splice plate of the wing, and follow-on actions, 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 correct corrosion of the upper splice plate of the wing, which could result in reduced structural integrity of the airplane.
89-06-05 R1: 89-06-05 R1 AVIONS MARCEL DASSAULT- BREGUET AVIATION (AMD-BA): Amendment 39-6151 as revised by Amendment 39-6412. Docket No. 89-NM-142-AD. Applicability: Model Mystere Falcon 50 and 900 series airplanes as listed in AMD-BA Service Bulletins F-50-208, Revision 1, and F-900-52, Revision 1, both dated July 25, 1989, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent inability to open the main landing gear (MLG) door for MLG emergency extension, accomplish the following: A. Prior to the accumulation of 1,000 landings on the MLG door emergency unlocking pin, or within 7 days after March 24, 1989 (the effective date of AD 89-05-05, Amendment 39-6151), whichever occurs later, verify the integrity of the MLG door emergency unlocking system by operating the manual opening system, in accordance with the instructions in the AMD-BA Falcon 50 Maintenance Manual Work Card 480.0, paragraph 3, or Falcon 900 Maintenance Procedure No. 32-120, as applicable. If the unlocking pin is broken or damaged, replace the pin with a serviceable pin of the same part number prior to further flight. B. Upon accumulation of 2,000 landings on the MLG door emergency unlocking pin, or within 50 landings after the effective date of this AD, whichever occurs later, repeat the inspection described in paragraph A., above, and continue to perform this inspection at intervals not to exceed 50 landings. C. Following the replacement of any unlocking pin with a new pin, repeat the inspections required by paragraphs A. and B., above. D. Prior to the accumulation of 2,000 landings on the airplane, or within 120 days after the effective date of this AD, whichever occurs later, modify the emergency release mechanism of each MLG door uplock unit in accordance with AMD-BA Service Bulletin F50-208 (F50-32-18), Revision 1, or F900-52 (F900-32-4), Revision 1, both dated July 25, 1989. Accomplishment of this modification constitutes terminating action for the inspections required by paragraphs A. through C. of this AD. 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 Falcon Jet Corporation, Customer Support Department, Teterboro Airport, Teterboro, New Jersey 07608. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This AD revises Amendment 39-6151, AD 89-06-05. This amendment (39-6412, AD 89-06-05 R1) becomes effective on January 12, 1990.
86-05-02: 86-05-02 UNITED INSTRUMENTS, INC.: Amendment 39-5317. Applies to altimeter Part Numbers 5934, 5934A, 5934M, 5934AM, 5934P, 5934PA, 5934PM, 5934PAM, 5934D, 5934PD, 5934AD, and 5934PAD with the following serial numbers: 6C461 thru 6C999 7C000 thru 7C999 8C000 thru 8C999 9C000 thru 9C999 0D000 thru 0D999 1D000 thru 1D999 2D000 thru 2D869 NOTE 1: This AD is applicable to pressure sensitive altimeters that do not have encoding capabilities. The affected altimeters were manufactured after February 1, 1985. Compliance: Required as indicated unless already accomplished. To prevent possible erroneous altitude information from being displayed to the pilot, accomplish the following: (a) For all altimeters that are installed in an aircraft, prior to further flight, (1) Check each installed altimeter or check the aircraft's permanent maintenance record to determine if the altimeter falls within the Serial Number designations set forth in this AD. The owner/operator of the aircraft may make this check. (2) If, as a result of this check, it is determined that the altimeter falls within these designations, check the altimeter by applying a slight outward pull on the adjustment knob while turning the knob and determine that the altitude indication pointers and the barometric pressure dial remain synchronized. (3) The holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) may conduct this check on any airplane owned or operated by him. The person accomplishing this must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. (4) If the altitude pointers do not move simultaneously with the barometric dial, prior to further flight remove the altimeter and return it to United Instruments, Inc., 3625 Comotara Avenue, Wichita, Kansas 67226, no later than July 1, 1986. Replacement altimeters must be serviceable units. NOTE 2: It is recommendedbut not required by this AD, that the above check for synchronized movement be accomplished each time the altimeter barometric pressure dial is adjusted. (b) Regardless of the results of the check specified in paragraph (a) of this AD, on or before July 1, 1986, for all affected altimeters installed in an aircraft, remove the altimeter and return it to United Instruments, Inc. at the above address. Replacement altimeters must be serviceable units. (c) For all affected altimeters not installed in an aircraft, prior to further use but no later than July 1, 1986, return the altimeter to United Instruments, Inc., at the above address, for examination and modification as required. (d) For each altimeter returned to United Instruments, Inc. per the instructions of paragraphs (a), (b) and (c) above, the examination and rework by United Instruments, Inc. will be identified by a yellow dot approximately 1/4 inch (6.4mm) diameter on the lower half of the rear case and the letter"M", approximately 1/8 inch (3.2mm) in height stamped on the data plate just before the word "altimeter". Units that have been reworked and so marked may be used as serviceable replacement parts. (e) Aircraft may be flown in accordance with Federal Aviation Regulation (FAR) 21.197 to a location where this AD can be accomplished. Prior to dispatch, set the altimeter to field elevation and do not reset in flight. (f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. United Instruments Service Bulletin No. 2, dated February 24, 1986, pertains to the subject of this AD. All persons affected by this directive may obtain copies of the documents referred to herein upon request to United Instruments, Inc., 3625 Comotara Avenue, Wichita, Kansas 67226, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on May 28, 1986, to all persons except those to whom it has already been made effective by priority letter AD from the FAA dated February 28, 1986, and is identified as AD 86-05-02.
98-20-36: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, that currently requires inspections for cracks of the fuselage, wings, and vertical stabilizer structures; and repairs or modifications, if necessary. That AD was prompted by reports of cracking in several areas of the fuselage, wings, and vertical stabilizer structure due to fatigue-related stress. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in reduced structural integrity of the fuselage, wing, and vertical stabilizer. This action provides for a new optional terminating action, for certain airplanes, and expands the applicability of the existing AD to include additional airplanes.
2019-03-28: We are superseding Airworthiness Directive (AD) 2016-07-23, which applied to all Airbus SAS Model A318 and A319 series airplanes; Model A320-211, A320-212, A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes; and Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232 airplanes. AD 2016-07-23 required, for certain airplanes, repetitive replacements of the fixed fairing upper and lower attachment studs of both the left-hand (LH) and right-hand (RH) main landing gear (MLG); and repetitive inspections for corrosion, wear, fatigue cracking, and loose studs of each forward stud assembly of the fixed fairing door upper and lower forward attachments of both the LH and RH MLG; and replacement if necessary. AD 2016-07-23 also provided an optional terminating modification for the repetitive replacements of the fixed fairing upper and lower attachment studs. This AD retains the requirements of AD 2016-07-23 and, for certain airplanes, requiresre-identification of the LH and RH MLG fixed fairing assemblies' part numbers. This AD was prompted by a determination that for some airplane configurations, associated fixed fairing assembly part numbers susceptible to fatigue cracking were not listed in certain service information required by AD 2016-07-23. In addition, we have determined that additional work is necessary to re- identify the fixed fairing assembly part [[Page 8599]] number on certain airplanes. We are issuing this AD to address the unsafe condition on these products.
96-24-06: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-24-06 that was sent previously to all known U.S. owners and operators of certain Cessna Model 560 series airplanes by individual letters. This AD requires revising the FAA-approved Airplane Flight Manual (AFM) to provide the flightcrew with limitations, operational procedures, and performance information to be used during approach and landing when residual ice is present or can be expected. This amendment is prompted by reports indicating that, while operating in icing conditions or when ice is on the wings, some of these airplanes have experienced uncommanded roll at a speed at (or slightly higher than) the speed at which the stall warning system is activated. The actions specified by this AD are intended to prevent uncommanded roll of the airplane during approach and landing when residual ice is present or can be expected.