Results
98-05-14: This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company Models T210N, P210N, and P210R airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
92-27-03: 92-27-03 DE HAVILLAND, INC.: Amendment 39-8436. Docket No. 92-NM-158-AD. Applicability: Model DHC-7 series airplanes; serial numbers 1 through 7, inclusive, and 9, 10, and 11; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the engine nacelles, accomplish the following: (a) Within 6 months after the effective date of this AD, conduct an inspection to determine whether rivets that secure the upper longerons in each inner engine nacelle have been installed, in accordance with de Havilland Service Bulletin 7-54-9, dated February 29, 1980. (1) If any rivets are missing, prior to further flight, accomplish Modification No. 7/1707, in accordance with the service bulletin. (2) If all rivets are detected, no further action is required by this AD. (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 the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspection and modification shall be done in accordance with de Havilland Service Bulletin 7-54-9, dated February 29, 1980. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on January 22, 1993.
98-05-15: This amendment adopts a new airworthiness directive (AD) that applies to SIAI Marchetti, S.r.1 Models SF600 and SF600A airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
98-05-10: This amendment adopts a new airworthiness directive (AD) that is applicable to Robinson Helicopter Company (Robinson) Model R44 helicopters. This action requires replacing the aluminum elbows that connect the oil cooler lines to the engine accessory case with steel elbows. This amendment is prompted by two reports of cracks that were discovered in aluminum elbows. The actions specified in this AD are intended to prevent failure of either the 45 degree or 90 degree aluminum elbows that connect the oil lines from the oil cooler to the engine accessory case, which would cause loss of engine oil, resulting in an engine failure and a subsequent forced landing.
85-21-07 R1: 85-21-07 R1 BEECH: Amendment 39-5295 as amended by 39-5637. Applies to Models 1900 (Serial Numbers UA-1 through UA-3) and 1900C (Serial Numbers UB-1 through UB-60) airplanes certificated in any category. Compliance: Required within 10 hours time-in-service after receipt of this AD, unless already accomplished. To ensure that required performance can be achieved for each approved combination of takeoff configuration, weight, altitude, and temperature, accomplish the following: (a) Revise Beech Model 1900/1900C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM), P/N 114-590021-3, in accordance with Model 1900 and 1900C interim Addendum to POH/AFM, P/N 114-590021-3, dated October 21, 1985. NOTE: The above cited interim Addendum was transmitted to Model 1900/1900C operators of record by Beech letter 52-85-1948, dated October 21, 1985. (b) Conduct further operations in accordance with the POH/AFM so revised. (c) The requirementsof paragraph (a) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. (d) The requirements of paragraphs (a), (b), and (c) do not apply to airplanes which have installed Beech Kit Part Number (P/N) 114-4013-1 S. Airplanes with this kit installed may operate in accordance with the limitations and procedures shown in Beech Model 1900/1900C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM), P/N 114- 590021-3. (e) An equivalent means of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to hereinupon request to Mr. Lou Gollin, Beech Aircraft Service Engineering, Department 52, P.O. Box 85, Wichita, Kansas 67201; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-5295 became effective May 6, 1986. This amendment, 39-5637, becomes effective on July 10, 1987.
92-19-04: 92-19-04 AIRBUS INDUSTRIE: Amendment 39-8362. Docket No. 91-NM-252-AD. Applicability: Model A300-B4-620, A310-221, A310-222, and A310-322 series airplanes, equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, or JT9D-7R4H1 series engines; and Model A300-B4-622, A300-B4-622R, and A310-324 series airplanes, equipped with Pratt and Whitney PW 4152 or PW 4158 series engines, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the airplane, accomplish the following: (a) Accomplish the requirements of paragraphs (a)(1), (a)(2), and (a)(3) of this AD as follows: For airplanes equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, and JT9D-7R4H1 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW7R4 71-90, Revision 2, dated May 14, 1992, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter JT9/71-00/SS:JDS:0-12-3-1. For airplanes equipped with Pratt and Whitney PW 4152 and PW 4158 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW4NAC 71-86, Revision 2, dated February 28, 1992, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter 4000/71.00/SS:TJF:0-12-03-1. (1) Prior to the accumulation of 500 hours time-in-service after the effective date of this AD, perform a visual inspection to detect cracks or a broken link in the forward engine mount thrust link, in accordance with Part 1 of the applicable service bulletin. (i) If no crack or broken link is found, repeat the visual inspection thereafter at intervals not to exceed 1,000 landings until the requirements of paragraph (a)(2) of this AD are accomplished. (ii) If any crack or a broken link is found as a result of the visual inspection, prior to further flight, replace the link with a serviceable part that has been inspected in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (a) of this AD. (2) At the next engine removal or within 4,000 hours time-in-service after the effective date of this AD, whichever occurs first, perform a initial etch inspection to detect cracks or a broken link in the forward engine mount thrust link, in accordance with the applicable service bulletin. (i) If no crack is found as a result of the initial etch inspection, reinstall the link assembly in accordance with the applicable service bulletin. No further action is required. (ii) If any crack or broken link is found as a result of the initial etch inspection, prior to further flight, replace the link with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (a) of this AD. (3) Replacement of the forward engine mount thrust link in accordance with the applicable service bulletin constitutes terminating action for the requirements of this AD. (b) Accomplish the requirements in paragraphs (b)(1), (b)(2), (b)(3), and (b)(4) of this AD as follows: For airplanes equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, and JT9D-7R4H1 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW7R4 71-100, Revision 1, dated July 25, 1991, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter JT9/71-00/SS:0-12-3-1. For airplanes equipped with Pratt and Whitney PW 4152 and PW 4158 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW4NAC 71-105, Revision 1, dated July 25, 1991, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter 4000/71-00/SS:TJF:0-12-03-1. (1) Prior to the accumulation of 500 hours time-in-service after the effective date of this AD, perform a visual inspection to detect cracks or forging laps in the aft engine mount beam assembly, in accordance with Part 1 of the applicable service bulletin. (i) If no crack or forging lap is found as a result of the visual inspection, repeat the visual inspection thereafter at intervals not to exceed 1,000 landings until the requirements of paragraph (b)(2) of this AD are accomplished. (ii) If any crack is found as a result of the visual inspection, prior to further flight, perform a dip etch and a spot fluorescent penetrant inspection to confirm the findings of cracks or forging laps, in accordance with Part 2 of the applicable service bulletin. If any finding of cracks or forging laps is confirmed, prior to further flight, replace the defective beam assembly with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (b) of this AD. As of the effective date of this AD, none of the aft beam assemblies listed in the applicable service bulletin shall be installed on any airplane. (2) Except as provided by paragraph (b)(3) of this AD, at the next engine removal or within 4,000 hours time-in-service after the effective date of this AD, whichever occurs first, perform a dip etch and a fluorescent penetrant inspection to detect cracks or forging laps in the aft engine mount beam assembly, in accordance with Part 2 of the applicable service bulletin. (i) If no crack or forging lap is found as a result of the dip etch and fluorescent penetrant inspection, reinstall the beam assembly in accordance with the applicable service bulletin. No further action is required. (ii) If any crack or forging lap is found as a result of the dip etch and fluorescent penetrant inspection, prior to further flight, replace the beam assembly with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (b) ofthis AD. (3) If the requirements of paragraph (b)(2) of this AD result in a dual engine removal, the dip etch and fluorescent penetrant inspection of one of the two aft engine mounts may be deferred to the next 4,000 hours time-in-service or engine removal, whichever occurs first, provided no crack or forging lap is found while accomplishing the visual inspections required by paragraph (b)(1) of this AD. If those inspections are deferred, repeat the visual inspection of the deferred aft engine mount, as required by paragraph (b)(1) of this AD, at intervals not to exceed 1,000 landings. (4) Replacement of the aft engine mount beam assembly, in accordance with the applicable service bulletin, constitutes terminating action for the requirements of paragraph (b) of this AD. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The inspection and replacement shall be done in accordance with the following Pratt and Whitney service bulletins, as applicable, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page PW4NAC 71-105, Revision 1, July 25, 1991, 1-19 1 July 25, 1991, 1-2 3, 6, 8, 11-16, 18 2 1 February 28, 1992 July 25, 1991PW4NAC 71-86, Revision 2, February 28, 1992 4-5, 7, 9-10, 17 Original May 10, 1991 1, 16-20 2, 4-5, 7, 10 2 Original May 14, 1992 May 10, 1991 PW7R4 71-90, Revision 2, May 14, 1992 3, 6, 8-9, 11-15 1 July 25, 1991 PW7R4 71-100, Revision 1, July 25, 1991 1, 4, 6-18 2-3, 5 1 Original July 25, 1991 May 10, 1991 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on November 17, 1992.
2012-12-03: We are superseding an existing airworthiness directive (AD) for all Rolls-Royce plc (RR) models RB211-Trent 970-84, 970B-84, 972- 84, 972B-84, 977-84, 977B-84, and 980-84 turbofan engines. That AD currently requires inspecting the intermediate-pressure (IP) shaft rigid coupling splines for wear resulting in rearward movement of the IP turbine. This AD requires the same inspections, and new inspections based on possible changes in wear rate. This AD was prompted by RR identifying wear beyond engine manual limits on the abutment faces of the splines. RR also determined that an additional IP shaft rigid coupling configuration requires inspection. We are issuing this AD to detect wear on the abutment faces of the splines, which could result in loss of disc integrity, an uncontained failure of the engine, and damage to the airplane.
2005-13-39: The FAA is superseding an existing airworthiness directive (AD), which applies to Airbus Model A321 series airplanes. That AD currently requires revising the Limitations section of the airplane flight manual to include an instruction to use Flap 3 for landing when performing an approach in conditions of moderate to severe icing, significant crosswind (i.e., crosswinds greater than 20 knots, gust included), or moderate to severe turbulence. This new AD requires replacing existing elevator and aileron computers (ELACs) with ELACs having either L83 or L91 software, as applicable, which terminates the requirements of the existing AD. This AD also requires a related concurrent action. In addition, this AD revises the applicability by removing airplanes with these ELAC software standards incorporated in production. This AD is prompted by issuance of mandatory continuing airworthiness information by a civil airworthiness authority. We are issuing this AD to prevent roll oscillationsduring approach and landing in certain icing, crosswind, and turbulent conditions, which could result in reduced controllability of the airplane.
75-05-07: 75-05-07 KING RADIO CORPORATION: Amendment 39-2100. Applies to Model KCS-55 Pictorial Navigation System (magnetic stabilized compass) units, specifically the Gyro Model KG-102 ( ), Part Number 060-0011-0, Serial Numbers 1000 to 1999 and all serial numbers preceded by the letter "P" and Indicator Models KI-525 ( ), Part Number 066-3029-00/01, Serial Numbers 1000 to 1999 and all serial numbers preceded by the letter "P". The Model KCS-55 systems may be installed on various types of aircraft. Compliance: Required as indicated, unless already accomplished. A) Within the next 25 hours' time in service after the effective date of this AD, check the aircraft compass system installed or the aircraft permanent maintenance record to determine if the KCS-55 pictorial navigation system is installed on the aircraft. B) If, as a result of determination required in Paragraph A of this AD, a KCS-55 pictorial navigation system is installed, check the indicator KI-525 ( ) to determineif the serial number falls within those noted in the applicability statement and if the unit has been modified and identified as Mod 1. Also, check the KG 102 gyro and determine if the serial number falls within those noted in the applicability statement and that the unit has been modified and identified as Mod 6. If both units are so identified with the modification number, make an appropriate entry in the aircraft records indicating compliance with this AD. C) If as a result of the determinations required by Paragraphs A and B of this AD unmodified KCS-55 Pictorial Navigation System units are installed, prior to further flight, install a placard on the instrument panel in clear view of the pilot which indicates: "KCS-55 PICTORIAL NAVIGATION SYSTEM IS NOT TO BE USED FOR PRIMARY HEADING OR IFR FLIGHT IF IT IS SOLE GYROSCOPIC HEADING SOURCE" and operate the aircraft in accordance with this limitation. D) On or before November 15, 1975, replace any KCS-55 pictorial navigation system units which fall within the Part Number and Serial Number designations set forth in the applicability statement with modified units which are identified in accordance with King Alert Service Bulletins KI 525-1 and KG 102-6 dated January 2, 1975, or subsequent revisions, as Mod 1 and Mod 6 respectively. When this paragraph has been complied with, Paragraph C of this AD is no longer applicable. E) Any alternative means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective February 28, 1975.
90-09-03: 90-09-03 MCDONNELL DOUGLAS: Amendment 39-6582. Docket No. 89-NM-136-AD. \n\n\tApplicability: Model DC-10-10 and -15 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the loss of the main landing gear brakes, accomplish the following: \n\n\tA.\tWithin 90 days after the effective date of this amendment, inspect Airplanes Braking Systems (formerly Loral, formerly Goodyear) brakes, part numbers 5000709-1, -3, -5, -7, and -8, for wear. Any brake worn more than 1.00 inch must be replaced, prior to further flight, with one within this limit. \n\n\tB.\tWithin 90 days after the effective date of this amendment, incorporate the 1.00 inch brake wear limit into the FAA-approved maintenance inspection program. \n\n\tC.\tWithin 120 days after the effective date of this amendment, inspect Airplanes Braking Systems (formerly Loral, formerly Goodyear) brakes, part numbers 5000709-1, -3, -5, -7, and -8, for wear. Anybrake worn more than 0.60 inch must be replaced, prior to further flight, with one within this limit. \n\n\tD.\tWithin 120 days after the effective date of this amendment, incorporate the 0.60 inch brake wear limit into the FAA-approved maintenance inspection program. \n\n\tE.\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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tF.\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\tThis amendment (39-6582, AD 90-09-03) becomes effective on May 29, 1990.
89-23-03: 89-23-03 EMPRESA BRASILEIRA DE AERONAUTICA, S.A. (EMBRAER): Amendment 39-6368. Docket No. 89-NM-86-AD. Applicability: Model EMB-120 series airplanes, as listed in EMBRAER Service Bulletin 120-034-0072, dated April 14, 1989, certificated in any category. Compliance: Required within 100 days after the effective date of this AD, unless previously accomplished. To prevent erratic glide slope information during IFR approaches, accomplish the following: A. Replace the Chelton glide slope antenna, P/N 17-21F6P3, with a Collins glide slope antenna type 37P5, P/N 522-0700-023, and install a pedestal-type support P/N 120-47294- 001, in accordance with EMBRAER Service Bulletin 120-034-0072, dated April 14, 1989. B. 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 beforwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. 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 EMBRAER, 276 S.W. 34th Street, Fort Lauderdale, Florida 33315. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia. This amendment (39-6368, AD 89-23-03) becomes effective on November 27, 1989.
2012-13-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a report of a ground fire which was fed by oxygen escaping from a damaged third crew person oxygen line and had started in the vicinity of an electrical panel. This AD requires replacing and changing the routing of the flexible oxygen hose of the third crew person oxygen line and modifying the entrance compartment assembly. We are issuing this AD to prevent the possibility of damage to the third crew person oxygen line and of an oxygen-fed fire in the airplane.
2012-12-10: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters with a certain generator control unit (GCU), to require replacing each affected GCU with an airworthy GCU. This AD was prompted by laboratory tests which revealed a potential fault in the overvoltage protection on a certain part-numbered GCU. The actions are intended to prevent failure of the overvoltage protection of the GCU, degraded performance of the electrical power generation and distribution systems, a fire, and subsequent loss of control of the helicopter.
98-04-45: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes, that currently requires revisions to the Airplane Flight Manual (AFM) to advise the flight crew of the need to perform daily checks to verify proper operation of the elevator control system, and to restrict altitude and airspeed operations under certain conditions. That AD also requires removal of all elevator flutter dampers. That AD was prompted by reports that the installation of certain shear pins may jam or restrict movement of the elevator. The actions specified by that AD are intended to prevent such jamming or restricting movement of the elevator and the resultant adverse effect on the controllability of the airplane. This amendment adds inspections of certain airplanes to detect deformation or discrepancies of the flutter damper hinge fittings and lug of the horizontal stabilizer, the elevator hinge/damper fitting, and the shear pin lugs; and requires replacement of discrepant parts with serviceable parts. This amendment also requires installation of new elevator flutter dampers, and replacement of shear pins and shear links with new, improved pins and links.
2010-10-03: This amendment adopts a new airworthiness directive (AD) for the Sikorsky Model S-92A helicopters. The AD requires replacing the main gearbox (MGB) filter bowl assembly with a two-piece MGB filter bowl assembly and replacing the existing mounting studs. The AD also requires inspecting the MGB lube system filters, the housing, the housing threads, and the lockring counterbore and repairing or replacing them as necessary. This amendment is prompted by tests indicating that an existing MGB filter bowl assembly can fail under certain loading conditions including those associated with a damaged MGB filter or mounting stud resulting from high frequency maintenance tasks. Testing of the improved MGB filter bowl assembly demonstrates a significant increase in strength and durability over the existing filter bowl. The actions specified by this AD are intended to prevent failure of the MGB filter bowl assembly due to failure of the mounting studs or the filter bowl, loss of oil from theMGB, failure of the MGB, and subsequent loss of control of the helicopter.
89-20-12: 89-20-12 BELL HELICOPTER TEXTRON, INC. (BHTI); HERCULES; OREGON HELICOPTERS; LENAIR CORPORATION; AND SOUTHWEST FLORIDA AVIATION: Amendment 39-6664. Docket No. 89-ASW-42-AD. Final copy of Priority Letter AD. Applicability: Model 204B, 205A, 205A-1, UH-1L, TH-1L, UH-1H helicopters, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the tail rotor hub assembly, which could result in loss of control and subsequent loss of the helicopter, accomplish the following: (a) Before further flight, determine the part number and serial number of the tail rotor hub assembly installed on the helicopter. (b) If the tail rotor hub assembly installed is P/N 204-011-801-121 and is identified with any serial number IT0001 through and including IT0010, remove and replace the assembly with an airworthy part before further flight. (c) If one of the tail rotor hub assemblies listed in paragraph (b) is found,report the helicopter registration, serial number, and hub assembly serial number to the Manager, Rotorcraft Certification Office, Federal Aviation Administration, Fort Worth, Texas, 76193-0170, telephone (817) 624-5170, within 10 days of the inspection. (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056.) (d) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the inspection and assembly replacement may be accomplished. (e) An alternate method of compliance, which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Certification Office, ASW-170, Federal Aviation Administration, Fort Worth, Texas 76193-0170, telephone (817) 624-5170. This amendment (39-6664, AD 89-20-12) becomes effective August 15, 1990, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 89-20-12, issued September 29, 1989, which contained this amendment.
2012-12-16: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of cracking of certain fuel access panels of the outer wing. This AD requires an external inspection, and if necessary an internal inspection, to determine if certain fuel access panels are installed, and replacement if necessary; optional repetitive inspections for cracking of the fuel access panels, and replacement if necessary, would defer the internal inspection; and eventual replacement of affected fuel access panels with new panels. We are issuing this AD to prevent cracking of fuel access panels, which could result in arcing and ignition of fuel vapor in the outer wing fuel tank during a lightning strike.
58-21-01: 58-21-01 LOCKHEED: Applies to All Models 049, 149, 649, 649A, 749, 749A, 1049- 54, 1049C, 1049D, 1049E, 1049G, and 1049H and 1649 Aircraft. Compliance required as indicated. This is a supplement to AD 58-20-03, in that it applies to an additional area of the pressure bulkhead (Station 1037) and to a greater number of aircraft. A recent inspection of a Model 1049E airplane with 10,500 hours logged time revealed extensive corrosion along W.L. 239 (approximately) between a wood strip and pressure diaphragm at the lavatory seat level. Reported corroded area was approximately 27 inches long by 5 inches wide. Accordingly, on all aircraft that have or once had lavatories in this area, accomplish the following: 1. Unless already accomplished per Lockheed wire FS/229080-W, within the next 50 flight hours thoroughly examine the aft side of the bulkhead for corrosion in the area of W.L. 239 from a height of 2 inches above to 2 inches below the centerline of rivet or screw attachments across the full width of the bulkhead. Probe the area with a blunt tool to detect advance stages of corrosion. If any evidence of corrosion is found, conduct inspection under step 3. immediately. 2. Unless already accomplished per Lockheed wire FS/229080-W, within 400 hours, inspect in accordance with step 3, or alternatively as follows: Remove 5/8-inch maximum diameter slugs from the pressure diaphragm by means of a hole saw or equivalent method. Take samples at approximately 6- to 7-inch spacing from the back side of the bulkhead across its full width at approximately W.L. 239. Do not cut samples from diaphragm area covered by stiffeners. If samples show any evidence of corrosion, conduct inspection in accordance with step 3. immediately. Holes in diaphragm may be plugged in accordance with negligible damage repair shown in applicable structural repair manual. 3. If corrosion is found as a result of steps 1. or 2., the following inspections shall be conducted immediately. If both steps 1. and 2. reveal no corrosion, the following inspection shall be conducted at the next block overhaul or within 4,000 flight hours whichever occurs first and at each block overhaul or 4,000-hour period thereafter. Remove toilet seats and other portions of installation as required. Peel back trim and insulation to expose trim strip and at least 2 inches of bulkhead web above and below trim strip, completely across bulkhead within each lavatory compartment. Remove trim strip and all paint, sealant and cement from the exposed area of web. Make close visual inspection for corrosion. 4. Replace any material or parts which show evidence of corrosion damage. Strip to bare metal, apply inhibitor, sealant, and paint to all exposed web areas. In applying this protection, if the sealant and protective materials noted in Lockheed SB/597 are used, further special inspection at 4,000-hour intervals may be discontinued and normal routine inspections resumed. 5. If corrosion is found, flight operations shall be restricted, pending repairs as follows: (a) Unpressurized flight is permissible if corrosion damage is found on the diaphragm as a result of inspection per steps 1. or 2. (Lockheed wire FS/229080-W, dated October 13, 1958, covers the same subject as this supplement.) (Lockheed Structural Repair Manuals, as applicable, cover acceptable repair methods.)
77-08-06: 77-08-06 MOONEY: Amendment 39-2877 as amended by Amendment 39-2903 is further amended by Amendment 39-2962. Applies to Models M20E (Serial Numbers 101 through 466, 470 through 1217, 1219, 1221, 1223 through 1308, 670001 through 670062, 690001 through 690073, 700001 through 700039, 700041 through 700043, 700045 through 700052, 700055, 700056, 700060, 700061, 21-0001 through 21-1180); M20F (Serial Numbers 670001 through 670363, 670365 through 670385, 670387 through 670482, 670484 through 670539, 680001 through 680206, 690001 through 690090, 690092, 700001 through 700061, 700063, 700066 through 700070, 700072, 22-0001 through 22-1437); M20J (Serial Numbers 24- 0001 through 24-0237) airplanes. Compliance required prior to further flight after the effective date of this AD except that the airplane may be flown in accordance with FAR 21.197 to a base where the removal can be performed. To prevent loss of engine oil accomplish the following: (a) Before the next flight of the affected airplanes, remove the engine cowl and visually check the engine oil cooler to determine whether it is a Stewart-Warner Model 8432H (S/N 001 and Up) 8432F (S/N 1610 through 1717). (1) If the oil cooler is not of the model and serial numbers listed above, make an entry in the aircraft maintenance records indicating that this Airworthiness Directive (AD) has been accomplished and the airplane may be returned to service. NOTE: If your airplane was manufactured prior to March 1, 1975, and your oil cooler has not been replaced since that date, then your airplane does not have a suspect oil cooler. (2) If the oil cooler is of a model and serial number listed above, before further flight after the effective date of this AD, the oil cooler must be removed and replaced with a serviceable Stewart- Warner Model 8432F-1 oil cooler, except that the airplane may be flown in accordance with FAR 21.197 to a base where the removal and replacement can be performed. A pilot may perform the visual checks outlined in items (a)(1) above pursuant to the provisions of FAR 43.3(h). NOTE: For the requirements regarding the listing of compliance and method of compliance with paragraphs (a)(1) and (a)(2) of this AD in the aircraft permanent maintenance record, see FAR 91.1973. (b) Deleted. (c) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. NOTE: Mooney Service Bulletin M20-203, dated July 7, 1977, pertains to this same subject. Amendment 39-2877 became effective on April 21, 1977, and was effective upon receipt for all recipients of the airmail letter dated April 15, 1977. Amendment 39-2903 became effective May 19, 1977, and was effective upon receipt for all recipients of the airmail letter dated May 16, 1977. This amendment 39-2962 becomes effective July 25, 1977, and was effective upon receipt for all recipients of the airmail letter dated July 8, 1977.
98-04-47: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Models TB9, TB10, and TB200 airplanes. This AD requires inspecting the main landing gear (MLG) support ribs for cracks, replacing MLG support ribs that have cracks beyond a certain level, and incorporating a certain MLG support rib reinforcement kit. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent MLG failure caused by cracks in the support ribs, which could result in loss of control of the airplane during landing operations.
2012-12-18: We are superseding an existing airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. That AD currently requires revising the Abnormal Procedures and Limitations sections of the Dassault F7X Airplane Flight Manual. This new AD requires a test of the power distribution control units (PDCU) cards and generator control units (GCU) cards to detect faulty components, and if any faulty components are found, replacing any affected PDCU or GCU card. This AD was prompted by a determination that additional actions are necessary to address the identified unsafe condition. We are issuing this AD to detect and correct a leakage failure mode of transient voltage suppression (TVS) diodes used on PDCU cards or GCU cards in the primary power distribution boxes (PPDB), which, in combination with other system failures, could lead to loss of controllability of the airplane.
2022-05-11: The FAA is adopting a new airworthiness directive (AD) for Viking Air Limited (type certificate previously held by Bombardier Inc.) Model DHC-3 airplanes with a certain wing strut assembly installed. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as fatigue damage of the wing struts. This AD requires a bolt hole eddy current inspection of the lug plate holes, a visual and fluorescent dye penetrant inspection of the lug fittings, and a visual and eddy current surface scan inspection of the wing strut assemblies. This unsafe condition could lead to failure of the wing strut, which could result in an in- flight breakup of the wing. The FAA is issuing this AD to address the unsafe condition on these products.
86-23-03: 86-23-03 PRATT & WHITNEY: Amendment 39-5455. Applies to Pratt & Whitney (PW) JT9D-7R4D, D1, E, and E1 turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent failure of the second stage high pressure turbine rotor (HPTR) airseal that can cause an uncontained engine failure, accomplish the following: (a) Remove from service, HPTR airseal Part Number (P/N) 5001413-01 or 798916 and replace with HPTR airseal P/N 803673 or 803674, respectively, or rework HPTR airseal P/N 5001413-01 or 798916 in accordance with PW Alert Service Bulletin (ASB) JT9D-7R4-72-318, dated October 25, 1986, or FAA approved equivalent, per the following schedule: (1) JT9D-7R4D1 and JT9D-7R4E1 series engines: (i) Within 400 cycles in service (CIS) after the effective date of this AD, for HPTR airseals with greater than 800 CIS since new on the effective date of this AD. (ii) Within 400 CIS after the effective date of this AD, or 800 CIS since new, whichever occurs later, for HPTR airseals with 800 CIS since new or less on the effective date of this AD. (2) JT9D-7R4D and JT9D-7R4E series engines: (i) Within 900 CIS after the effective date of this AD, for HPTR airseals with greater than 1,600 CIS since new on the effective date of this AD. (ii) Within 900 CIS after the effective date of this AD, or 1,600 CIS since new, whichever occurs later, for HPTR airseals with 1,600 CIS since new or less on the effective date of this AD. (b) Remove first stage high pressure turbine cooling (HPTC) airduct assembly, P/N 796123, 796975, or 796746, and replace with HPTC airduct assembly, P/N 804146, 804145, or 804148, respectively, or rework HPTC airduct assembly, P/N 796123, 796975, or 796746, in accordance with PW ASB JT9D-7R4-72-318, dated October 25, 1986, or FAA approved equivalent, concurrent with accomplishing paragraph (a) above. (c) Modify the first stage turbine rotor assembly, P/N 792041, 792931,795121, or 801821, by removing two units each of bolt, P/N 746130; washer, P/N 151178; and nut, P/N 341859; and redistributing the remaining units in accordance with PW ASB JT9D-7R4-72-318, dated October 25, 1986, or FAA approved equivalent, concurrent with accomplishing paragraph (a) above. 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. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, may adjust the compliance times specified in this AD. Pratt & Whitney ASB JT9D-7R4-72-318, dated October 25, 1986, identifiedand 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 copies upon request to Pratt & Whitney, Commercial Products Division, 400 Main Street, East Hartford, Connecticut 06108. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 86-ANE-42, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on December 8, 1986.
98-04-15: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc., (formerly Garrett Engine Division, Garrett Turbine Engine Company and AiResearch Manufacturing Company of Arizona) TPE331 series turboprop and TSE331 turboshaft engines, that requires replacement or radiographic inspection, and replacement, if necessary, of certain third stage turbine stators with serviceable parts. This amendment is prompted by a report of an outer band weld that cracked subsequent to a radiographic inspection required by a previous AD. The actions specified by this AD are intended to prevent third stage turbine wheel separation due to thermal fatigue cracking and shifting of the third stage turbine stator, which could contact the third stage turbine wheel and result in an uncontained engine failure and damage to the aircraft.
87-02-08: 87-02-08 BEECH: Amendment 39-5568. Applies to the following serial-numbered airplanes certificated in any category: MODEL SERIAL NUMBERS A23-19, 19A, M19A and B19 MB-1 thru MB-520 B19 Sport 150 MB-521 thru MB-905 23, A23, A23A, B23, C23 M-1 thru M-1361 C23 Sundowner 180 M-1362 thru M-2156, M-2158 thru M- 2392 A23-24, A24 MA-1 thru MA-368 A24R MC-2 thru MC-95 A24R, B24R, C24R Sierra 200 MC-96 thru MC-795 Compliance: Required prior to further flight on all airplanes and each 100 hours time-in- service (TIS) thereafter for normal and utility category airplanes, and each 25 hours TIS thereafter for acrobatic category airplanes, unless already accomplished. To preclude failure of the fasteners securing the stabilator hinge assemblies and subsequent loss of pitch control, accomplish the following: (a) Visually inspect the fasteners securing the stabilator hinge assemblies to the fuselage for looseness or failure in accordance with the "ACCOMPLISHMENT INSTRUCTIONS" in Beech Service Bulletin No. 2182, issued February 1987. (b) If any fasteners are found loose or failed when conducting the inspections required in paragraph (a) above, prior to further flight, replace all fasteners securing both the right and left hinge assemblies to the fuselage in accordance with the above-referenced service bulletin. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent method of compliance with this AD may be used when approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration (FAA), Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Beech Aircraft Corporation, Commercial Service Department, P.O. Box 85, Wichita, Kansas 67201; or may examine the document(s) referred to herein at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on March 4, 1987, to all persons except those to whom it has already been made effective by priority letter from the FAA dated January 27, 1987, and is identified as AD 87-02-08.