Results
2010-16-03: We are adopting a new airworthiness directive (AD) for certain Model MD-11 and MD-11F airplanes. This AD requires revising the airplane flight manual to advise the flightcrew to use certain procedures during descent in certain icing conditions. This AD results from reports of several in-flight engine flameouts, including multiple dual engine flameout events, in ice-crystal icing conditions. We are issuing this AD to ensure that the flightcrew has the proper procedures to follow in certain icing conditions. These certain icing conditions could cause a multiple engine flameout during flight with the potential inability to restart the engines, and consequent forced landing of the airplane.
99-19-23: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-19-23 which was sent previously to all known U.S. owners and operators of Eurocopter France Model EC 120B helicopters by individual letters. This AD requires, at specified time intervals, inspecting the engine coupling tube for cracks and replacing any cracked engine coupling tube with an airworthy engine coupling tube. This amendment is prompted by the discovery, during routine maintenance inspections, of three cracked engine coupling tubes caused by structural resonance. The actions specified by this AD are intended to detect a crack in the engine coupling tube which could result in coupling failure, loss of engine drive, and a subsequent forced landing.
99-21-02: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-30, SD3-60, SD3-SHERPA, and SD3-60 SHERPA series airplanes, that requires detailed visual and borescopic inspections to detect corrosion of the engine mounting tube assembly, and replacement of corroded parts with new or serviceable parts. 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 failure of the engine mounting tube assembly, which could result in loss of the engine in flight.
2022-16-04: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation (Gulfstream) Model GV and GV-SP airplanes. This AD was prompted by corrosion of the horizontal stabilizer lower bonded skin assemblies. This AD requires inspecting the horizontal stabilizer lower skin and associated bonded doublers and bonded stringers, repairing any area with corrosion beyond allowable damage limits, and incorporating revisions to the airworthiness limitations section (ALS) in the existing aircraft maintenance manual (AMM) or progressive maintenance program. The FAA is issuing this AD to address the unsafe condition on these products.
93-16-07: 93-16-07 BRITISH AEROSPACE: Amendment 39-8664. Docket 93-NM-31-AD. Applicability: Model BAe 146 series airplanes; on which Fairey Hydraulics airbrake servo-valve assembly, part number 3799H1, has been installed; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent malfunction of the airbrake; this could result in uncommanded airbrake extension or retraction, which, subsequently, could adversely affect airplane performance, accomplish the following: (a) Within 90 days after the effective date of this AD, perform a visual inspection to determine whether Abex servo-valve, part number 72189, has been installed and to identify the serial number on the Abex servo-valve, in accordance with British Aerospace BAe 146 Inspection Service Bulletin S.B. 27-133, dated January 31, 1992. (1) If an Abex servo-valve, part number 72189, has been installed, having a serial number listed in Table I of the service bulletin: Prior to further flight, accomplish the requirements of paragraphs (a)(1)(i) and (a)(1)(ii) of this AD. (i) Remove the existing servo-valve assembly in accordance with the service bulletin. (ii) Perform a visual inspection to detect metallic debris in the filter mesh in the servo-valve in accordance with the service bulletin. If any debris is detected, replace the currently installed airbrake actuator with a new or serviceable airbrake actuator, and install a new or serviceable servo-valve assembly in accordance with the service bulletin. (2) If an Abex servo-valve has been installed and has a serial number listed in Table 2 of the service bulletin: Prior to further flight, reidentify the servo-valve in accordance with the service bulletin. (3) If an Abex servo-valve has been installed and has a serial number not listed in either Table 1 or 2 of the service bulletin: No further action is required by this AD. (b) As of the effective date of this AD, no FaireyHydraulics airbrake servo-valve assembly, part number 3799H1, shall be installed on any airplane unless that airbrake servo-valve assembly is in compliance with the requirements 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, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (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, removal, replacement, and reidentification shall be done in accordance with British Aerospace BAe 146 Inspection Service Bulletin S.B. 27-133, dated January 31, 1992, which includes Appendix A1 to Service Bulletin S.B. 27-133, dated January 31, 1992. 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 British Aerospace, Inc., Avro Division, 22070 Broderick Drive, Sterling, Virginia 20166. 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 October 4, 1993.
93-14-20: 93-14-20 PRATT & WHITNEY: Amendment 39-8645. Docket No. 91-ANE-05. Applicability: Pratt & Whitney (PW) JT9D-59A, -70A, -7Q, and -7Q3 turbofan engines installed on, but not limited to Boeing 747, McDonnell Douglas DC-10, and Airbus A300 aircraft, in which the following high pressure turbine (HPT) stage 2 vane assemblies, identified by vane cluster assembly part numbers, are installed: 743772, 774872, 806272, 807372, 807772, 807072, and 808372. Compliance: Required as indicated, unless previously accomplished. To prevent uncontained HPT stage 2 blade fractures or lenticular airseal failures, accomplish the following: (a) For engines that have not incorporated the requirements of PW Service Bulletin (SB) 5566, Revision 5, dated August 10, 1990, and the requirements of PW SB 5428, Revision 3, dated March 12, 1984, borescope inspect the HPT stage 2 vanes in accordance with the Accomplishment Instructions of PW SB 5667, Revision 2, dated June 11, 1992, and in accordance withthe criteria identified in the applicable PW Maintenance Manual (MM) listed in paragraph (c) of this AD, prior to accumulating 1,000 hours time in service (TIS) since vane installation, or within the next 125 hours TIS after the effective date of this AD, whichever occurs later, and remove from service, prior to further flight, second stage turbine vanes exhibiting distress beyond serviceable limits. (b) For engines that have incorporated the requirements of PW SB 5566, Revision 5, dated August 10, 1990, and PW SB 5428, Revision 3, dated March 12, 1984, borescope inspect the HPT stage 2 vanes in accordance with the Accomplishment Instructions of PW SB 5667, Revision 2, dated June 11, 1992, and in accordance with the criteria identified in the applicable PW MM listed in paragraph (c) of this AD, prior to accumulating 2,000 hours total part TIS since new on the entire set of vanes, or within 1,000 hours TIS since vane installation, or within the next 125 hours TIS after the effectivedate of this AD, whichever occurs later, and remove from service, prior to further flight, second stage turbine vanes exhibiting distress beyond serviceable limits. (c) Thereafter, inspect the HPT stage 2 vanes in accordance with the criteria identified in the following PW MMs, and remove from service, prior to further flight, HPT stage 2 vanes exhibiting distress beyond serviceable limits. Engine Models MM Part Number/ Revision Date Section/Table JT9D-7Q/7Q3 783777/December 25, 1989 72-00-00/604A JT9D-59A/-70A 783778/April 25, 1990 72-00-00/605A JT9D-59A 783779/September 15, 1989 72-00-00/605 (d) 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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal 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 Engine Certification Office. (e) 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. (f) The inspections shall be done in accordance with the following service document: Document No. Pages Issue Date PW SB No. 5667 1-6 Revision 2 June 11, 1992 Total pages: 6 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 Pratt & Whitney, Publications Department, 400 Main Street, East Hartford, CT 06108. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on August 27, 1993.
98-17-01 R1: This amendment revises an existing airworthiness directive (AD), applicable to AlliedSignal Inc. TFE731 series turbofan engines, that currently requires installation of an improved flexible (flex) fuel tube. This amendment clarifies that installation of the improved flex fuel tube and that the use of a clamp on the original rigid fuel tube are optional for engines installed on Learjet 35, 36, and 55 series airplanes. This amendment is prompted by confusion from operators regarding the applicability of these Learjet engine installations. The actions specified by this AD are intended to prevent cracking of the fuel tube and the subsequent leakage of fuel on or around electrical components, which can cause an engine fire.
92-26-01: 92-26-01 CASA: Amendment 39-8428. Docket No. 92-NM-141-AD. Applicability: All Model CN-235, CN-235-100, and CN-235-200 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent flap separation and loss of roll control due to unsymmetrical wing surfaces, accomplish the following: (a) Perform detailed visual inspections of the flap track support structure to detect cracks and corrosion in accordance with CASA Maintenance Instructions 235-58, dated November 21, 1991, at the intervals specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. (1) For airplanes that have accumulated 2,000 hours time-in-service or less as of the effective date of this AD: Within 12 months after the effective date of this AD, or at the next "C" check, whichever occurs first, and thereafter at intervals not to exceed 12 months. (2) For airplanes that have accumulated more than 2,000 hours time-in-service as of the effective date of this AD: Within 100 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 12 months. (b) If cracks or corrosion are found as a result of the inspections required by paragraph (a) of this AD, prior to further flight, replace cracked or corroded parts in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (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, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any,may be obtained from the Standardization Branch, ANM-113. (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 inspections shall be done in accordance with CASA Maintenance Instructions 235-58, dated November 21, 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 Construcciones Aeronauticas S.A., Getafe, Madrid, Spain. 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 January 12, 1993.
2014-01-03: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aerosystems Model 340A (SAAB/SF340A) and SAAB 340B airplanes modified by Supplemental Type Certificate SA7971SW. This AD was prompted by reports of smoke, a burning odor, and possible fire in the flight deck and cabin of the airplane, which was caused by brushes wearing beyond their limits in the air conditioning motor. This AD requires an inspection to determine if a certain air compressor motor is installed, an inspection to determine the age of a certain compressor hour meter since new or overhauled, and repetitive replacement of the brushes on affected air conditioning compressor motor units. As an option to the replacement, this AD allows pulling the air conditioning circuit breaker and adding a placard. We are issuing this AD to detect and correct worn brushes contacting the commutator, which could result in a fire under the cabin floor with no means to detect or extinguish the fire.
96-18-08 R1: 96-18-08 R1 PRATT & WHITNEY: Amendment 39-10857. Docket 95-ANE-37. Revises AD 96-18-08, Amendment 39-9732. Applicability: Pratt & Whitney Models PW2037, PW2037(M), PW2040, PW2240, and PW2337 turbofan engines, installed on but not limited to, Boeing 757 series and Ilyushin IL96 series aircraft. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (o) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent high pressure turbine (HPT) or low pressure turbine (LPT) failure, which may result in an uncontained engine failure and possible damage to the aircraft, accomplish the following: (a) Remove from service 1st stage HPT disks, Part Number (P/N) 1A5301, prior to exceeding 5,000 total part cycles since new (TPC), if installed with blade retaining plate, P/N 1A6998, and replace with serviceable parts. If blade retaining plate, P/N 1A6998, has not been installed on disk, P/N 1A5301, the disk may accumulate 15,000 TPC prior to removal from service. (b) Remove from service 1st stage HPT blade retaining plates, P/N 1A6998, prior to exceeding 5,000 TPC, and replace with serviceable parts. If rework is accomplished prior to exceeding 5,000 TPC in accordance with the Accomplishment Instructions of PW Alert Service Bulletin (ASB) No. PW2000 A72-82, Revision 1, dated April 25, 1986; Revision 2, dated July 17, 1986; Revision 3, dated November 7, 1986; or Revision 4, dated June 18, 1987, and reidentified as assembly P/N 1B2373, the blade retaining plate may accumulate 15,000 TPC prior to removal from service. (c) Remove from service 2nd stage HPT blade retaining plates, P/N 1B0450, prior to exceeding 7,000 TPC, and replace with serviceable parts. (d) Remove from service 2nd stage HPT blade retaining plates, P/N 1B0945 (assembly P/N 1B0947), and replace with serviceable parts, in accordance with the Accomplishment Instructions of PW ASB No. PW2000 A72-228, Revision 2, dated May 10, 1988; Revision 3, dated August 25, 1988; or Revision 4, dated November 9, 1988, as follows: (1) Prior to exceeding 5,000 TPC, for retaining plates that have not been inspected in accordance with the Accomplishment Instructions of the above ASB prior to 3,000 TPC. (2) Prior to exceeding 8,000 TPC, for retaining plates that have been inspected in accordance with the Accomplishment Instructions of the above ASB prior to 3,000 TPC. (e) Remove from service 2nd stage HPT hubs, P/N's 1A8302, 1B1002, 1B1202, or 1B4902 prior to exceeding 7,500 TPC, and replace with serviceable hubs. Hubs may accumulate 15,000 TPC prior to removal from service if they are inspected at intervals that do not exceed 6,000 cycles in service since last inspection, in accordance with the Accomplishment Instructions of PW Service Bulletin (SB) No. PW2000 72-450, Original, dated March 13, 1992; Revision 1, dated March 26, 1992; Revision 2, dated April 7, 1992; Revision 3, dated May 29, 1992; Revision 4, dated August 28, 1992; ASB No. PW2000 72-450, Revision 5, dated May 28, 1994; or Revision 6, dated July 9, 1996. (f) Remove from service all suspect 2nd stage HPT hubs, P/N 1B6602, prior to exceeding 7,500 TPC, and replace with serviceable hubs. The suspect hubs are identified at the assembly level, P/N 1B6232, in Section 1, Planning Informationcontained in PW SB No. PW2000 72-501, dated September 30, 1993. Hubs may accumulate 15,000 TPC prior to removal from service if hub assemblies are inspected prior to 7,500 TPC to verify scarf cut blades are installed and to inspect the blade platform rail fillet radii dimensions, in accordance with the Accomplishment Instructions of PW SB No. PW2000 72-501, dated September 30, 1993. Hub assemblies found with non-scarf cut blades must be reinspected at intervals not to exceed 6,000 TPC since last inspection. Blades found with under minimum rail fillet radii dimensions must be scrapped. (g) Remove from service HPT lenticular airseal, P/N 1A8209, prior to exceeding 4,000 TPC, and replace with serviceable airseals. Airseals may accumulate 15,000 TPC prior to removal from service if: (1) Inspected prior to exceeding 4,000 TPC, and thereafter inspected at intervals not to exceed 250 cycles in service since last inspection, in accordance with Compliance Paragraph E of the Accomplishment Instructions of PW ASB No. PW2000 A72-220, Revision 3, dated April 13, 1989, or Revision 4, dated September 20, 1989; or (2) The 2nd stage HPT case and vane assembly is reworked and reidentified prior to exceeding 4,000 TPC, in accordance with the Accomplishment Instructions of PW SB No. PW2000 72-233, Revision 2, dated September 27, 1988, or Revision 3, dated May 30, 1989. (h) For PW2037, PW2037(M), and PW2337 model engines, remove from service 4th stage LPT disks, P/N's 8A1024, 8A1534, or 8A2137 prior to exceeding 17,000 TPC, and replace with serviceable disks. (i) For PW2040 and PW2240 model engines, remove from service 4th stage LPT disks, P/N's 8A1534 or 8A2137, prior to exceeding 15,000 TPC, and replace with serviceable disks. (j) Remove from service 3rd stage LPT airsealing ring supports, P/N 8A1783, and replace with serviceable parts, as follows: (1) For PW2040 and PW2240 model engines, prior to exceeding 15,000 TPC. (2) For PW2037, PW2037(M), and PW2337 model engines, prior to exceeding 17,000 TPC. Airsealing ring supports may accumulate 20,000 TPC prior to removal from service if they were fluorescent penetrant inspected in accordance with Section 72-53-00 of PW2000 Engine Manual, P/N 1A6231. (k) For PW2037, PW2037(M), and PW2337 model engines, remove from service prior to exceeding 17,000 TPC, and replace with serviceable parts, as follows: (1) 4th stage LPT airseal, P/N's 8A1014 or 8A1805. (2) 5th stage LPT airseal, P/N's 8A1015 or 8A1806. (3) 7th stage LPT airseal, P/N's A8A1017, A8A1808, 8A2097, or A8A2097. (l) Parts listed in paragraph (k) of this AD may accumulate 20,000 TPC prior to removal from service if they were fluorescent penetrant inspected for cracks between 12,000 TPC and 17,000 TPC in accordance with Section 72-53-00 of PW2000 Engine Manual, P/N 1A6231. (m) For PW2040 and PW2240 model engines, remove from service prior to exceeding 15,000 TPC, and replace with serviceable parts, as follows:(1) 4th stage LPT airseal, P/N's 8A1014 or 8A1805. (2) 5th stage LPT airseal, P/N's 8A1015 or 8A1806. (3) 7th stage LPT airseal, P/N's A8A1017, A8A1808, 8A2097, or A8A2097. (n) Parts listed in paragraph (m) of this AD may accumulate the following TPC prior to removal if they were fluorescent penetrant inspected for cracks between 10,000 TPC and 15,000 TPC in accordance with Section 72-53-00 of PW2000 Engine Manual, P/N 1A6231: (1) 4th stage LPT airseal, P/N's 8A1014 or 8A1805, prior to exceeding 18,000 TPC. (2) 5th stage LPT airseal, P/N's 8A1015 or 8A1806, prior to exceeding 19,000 TPC. (3) 7th stage LPT airseal, P/N's A8A1017, A8A1808, 8A2097, or A8A2097, prior to exceeding 20,000 TPC. (o) An alternative method of compliance or adjustment of the initial compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. Operators shall submit their requests through an appropriate FAA PrincipalMaintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Engine Certification Office. (p) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (q) The actions required by this AD shall be done in accordance with the following PW service documents: Document No Pages Revision Date ASB No. PW2000 A72-82 1 1 April 25, 1986 2-6 Original June 7, 1985 7-9 1 April 25, 1986 10 Original June 7, 1985 11 1 April 25, 1986 Total Pages: 11. ASB No. PW2000 A72-82 1 2 July 17, 1986 2-6 Original June 7, 1985 7-9 1 April 25, 1986 10 Original June 7, 198511 2 July 17, 1986 Total Pages: 11. ASB No. PW2000 A72-82 1-4 3 November 7, 1986 5,6 Original June 7, 1985 7-14 3 November 7, 1986 Total Pages: 14 ASB No. PW2000 A72-82 1 4 June 18, 1987 2-4 3 November 7, 1986 5,6 Original June 7, 1985 7-12 3 November 7, 1986 13 4 June 18, 1987 14 3 November 7, 1986 Total Pages: 14. ASB No. PW2000 A72-228 1 2 May 10, 1988 2 Original July 6, 1987 3 2 May 10, 1988 4 1 March 29, 1988 5-26 2 May 10, 1988 Total Pages: 26. ASB No. PW2000 A72-228 1 3 August 25, 1988 2 Original July 6, 1987 3 2 May 10, 1988 4 3 August 25, 1988 5-19 2 May 10, 1988 20 3 August 25, 1988 21,22 2 May 10, 1988 23 3 August 25, 1988 24-26 2 May 10, 1988 Total Pages: 26. ASB No. PW2000 A72-228 1 4 November 9, 1988 2 Original July 6, 1987 3 4 November 9, 1988 4 3 August 25, 1988 5-19 2May 10, 1988 20 3 August 25, 1988 21,22 2 May 10, 1988 23 3 August 25, 1988 24-26 4 November 9, 1988 Total Pages: 26. SB No. PW2000 72-450 1-26 Original March 13, 1992 Total Pages: 26. SB No. PW2000 72-450 1 1 March 26, 1992 2-11 Original March 13, 1992 12,13 1 March 26, 1992 14,15 Original March 13, 1992 16,17 1 March 26, 1992 18-21 Original March 13, 1992 22,23 1 March 26, 1992 24,25 Original March 13, 1992 26 1 March 26, 1992 Total Pages: 26. SB No. PW2000 72-450 1 2 April 7, 1992 2,3 Original March 13, 1992 4,5 2 April 7, 1992 6-11 Original March 13, 1992 12 1 March 26, 1992 13 2 April 7, 1992 14,15 Original March 13, 1992 16,17 1 March 26, 1992 18-21 Original March 13, 1992 22,23 1 March 26, 1992 24,25 Original March 13, 1992 26 1 March 26, 1992 Total Pages: 26. SB No. PW2000 72-450 1-5 3 May29, 1992 6-11 Original March 13, 1992 12 1 March 26, 1992 13 3 May 29, 1992 14 Original March 13, 1992 15-29 3 May 29, 1992 Total Pages: 29. SB No. PW2000 72-450 1 4 August 28, 1992 2-5 3 May 29, 1992 6-11 Original March 13, 1992 12 1 March 26, 1992 13 3 May 29, 1992 14 Original March 13, 1992 15 4 August 28, 1992 16 3 May 29, 1992 17 4 August 28, 1992 18-29 3 May 29, 1992 Total Pages: 29. ASB No. PW2000 72-450 1 5 May 28, 1994 2 4 May 28, 1994 3-5 3 May 29, 1992 6-11 Original March 13, 1992 12 1 March 26, 1992 13 3 May 29, 1992 14 Original March 13, 1992 15 4 August 28, 1992 16 3 May 29, 1992 17 4 August 28, 1992 18-29 3 May 29, 1992 Total Pages: 29. ASB No. PW2000 72-450 1 6 July 9, 1996 2 4 May 28, 1994 3-5 3 May 29, 1992 6-11 Original March 13, 1992 12 1 March 26, 1992 133 May 29, 1992 14 Original March 13, 1992 15 4 August 28, 1992 16 3 May 29, 1992 17 4 August 28, 1992 18-28 3 May 29, 1992 29 6 July 9, 1996 Total Pages: 29. SB No PW72-501 1-12 Original September 30, 1993 Total Pages: 12. ASB No. PW2000 A72-220 1 3 April 13, 1989 2 1 July 29, 1987 3-26 3 April 13, 1989 Total Pages: 26. ASB No. PW2000 A72-220 1 4 September 20, 1989 2 1 July 29, 1987 3-6 3 April 13, 1989 7-9 4 September 20, 1989 10-16 3 April 13, 1989 17-27 4 September 20, 1989 Total Pages: 27. SB No. PW2000 72-233 1,2 2 September 27, 1988 3-7 Original August 7, 1987 8 1 January 22, 1988 9,10 2 September 27, 1988 Total Pages: 10. SB No. PW2000 72-233 1-4 3 May 30, 1989 5 Original August 7, 1987 6 3 May 30, 1989 7 Original August 7, 1987 8 1 January 22, 1988 9,10 3 May 30, 1989 Total Pages: 10.The incorporation by reference of these service documents was approved previously by the Director of the Federal Register as of November 29, 1996 (61 FR 50984, September 30, 1996). Copies may be obtained from Pratt & Whitney, Publications Department, Supervisor Technical Publications Distribution, M/S 132-30, 400 Main St., East Hartford, CT 06108; telephone (860) 565-7700, fax (860) 565-4503. Copies may be inspected at the FAA, New England Region, Office of Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (r) This amendment becomes effective on November 10, 1998.
2014-04-03: We are adopting a new airworthiness directive (AD) for all Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as broken control column attachment bolts. We are issuing this AD to require actions to address the unsafe condition on these products.
2014-03-19: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -800, -900, and -900ER series airplanes modified by particular supplemental type certificates (STCs). This AD was prompted by reports of cracks found during inspections of the in-flight entertainment system radome assembly. This AD requires repetitive detailed inspections for cracks in the radome assembly, and replacement of the radome if necessary. We are issuing this AD to detect and correct cracks in the in-flight entertainment system radome assembly, which could result in the radome (or pieces) separating from the airplane and striking the tail, and consequently reducing the controllability of the airplane.
54-16-01: 54-16-01 SIKORSKY: Applies to All Model S-55 Helicopters. Compliance required as indicated. 1. (a) The rear accessory covers of main transmission S14-35-4000 and S14- 35-4300 should be inspected for cracks in the areas surrounding the points of attachment of the generator to the cover. Prior to the inspection, the paint in these areas should be removed. The inspections should be accomplished by the dye penetrant method. Covers found with cracks should be replaced immediately. These inspections are to be accomplished at every intermediate inspection. (b) Vibration isolators S14-35-4442 and S14-35-4443 have been designed by the manufacturer to prevent further failures. When these parts are installed in accordance with Sikorsky Information Circular No. 1435-443, the inspection outlined in item 1. (a) will be required at every major inspection for the first two inspections and then at every second major inspection if the cover has been operated without the isolator.If the cover has never been operated without the isolator, the inspection should be accomplished at the regular transmission overhaul period. (c) The retirement time for vibration isolators is specified in Sikorsky Information Circular S14-00-354, Rev. Z. 2. (a) The upper and lower ends of the main transmission support assembly, S14-20-2503, both fore and aft, must be inspected visually for cracks at every intermediate inspection. Particular attention should be directed at the underside of the attachment points, the welded joints and the small drive screws. Assemblies found with cracks are to be replaced immediately. (b) Prior to or at the next intermediate inspection and at every transmission overhaul thereafter, the S14-20-2503 support assemblies must be subjected to a Magnaflux inspection. Any cracks detected are cause for replacement. 3. The forward and aft lugs, to which the S14-20-2503 supports are attached, on the upper housing of the main transmissionmust be inspected at every major inspection. This inspection should be directed at each face of each lug in the area surrounding the bushing. Any crack detected is cause for replacement. 4. (a) The main rotor control servo brackets, S14-40-2113, S14-40-2143 and S14-40-2411 should be inspected for cracks in the area of the bracket ears. Prior to the inspection, all paint should be removed. The inspections should be accomplished by the dye penetrant method. Parts found with cracks should be replaced immediately. The exposed surfaces of brackets found satisfactory for return to service should be protected with several coats of zinc chromate primer. Extreme care should be taken in the installation procedure of either new or old brackets. These inspections are to be accomplished every 30 hours. (b) The inspections of 4. (a) will no longer be necessary when steel servo brackets S14-40-2415 are installed in accordance with Sikorsky Service Information Circular No. 1440-457 dated March 24, 1954. 5. The main rotor scissors bracket assembly S10-14-1447, should be inspected for sufficient edge distance at the bolt hole through which the scissors assembly S10-10-4350, is secured. A minimum edge diameter of 5/32 inch is allowable. Any S10-10-1447 brackets with less than 5/32-inch edge distance should be replaced. These inspections are to be performed on those helicopters with the S10-10-1400 Timken rotor head and are to be accomplished every 30 hours. (Sikorsky Service Information Circular No. 1435-383 dated September 3, 1953, as amended by revision A dated April 28, 1954, and revision B dated June 18, 1954, covers the same subject, except that section II of the Circular is amended by paragraph 1. (c).) This supersedes AD 53-25-02.
93-16-11: 93-16-11 BRITISH AEROSPACE: Amendment 39-8669. Docket 93-NM-33-AD. Applicability: Model 146-100A, -200A, and -300A series airplanes; equipped with Hosiden Besson Limited "Cybertone" smoke warning horns; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a fire in the lavatory from not being discovered and extinguished promptly, accomplish the following: (a) Within 5 months after the effective date of this AD, modify the smoke warning horns for the forward and aft lavatory smoke detectors in accordance with British Aerospace Modification Service Bulletin SB.26-32-36128A, dated April 30, 1992. (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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal MaintenanceInspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (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 modification shall be done in accordance with British Aerospace Modification Service Bulletin SB.26-32-36128A, dated April 30, 1992. 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 British Aerospace, Inc., Avro Division, 22070 Broderick Drive, Sterling, Virginia 20166. 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. (e) This amendment becomes effective on October 13, 1993.
2022-12-05: The FAA is superseding Airworthiness Directive (AD) 2020-26- 01, which applied to all Airbus SAS Model A318-111, -112, -121, and - 122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; and Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes. AD 2020-26-01 required repetitive general visual inspections of the affected main landing gear (MLG) sliding tubes for cracks, and replacement if necessary. This AD was prompted by reports of cracks found on MLG sliding tubes that may have been subject to improperly performed magnetic particle inspection. This AD requires repetitive general visual inspections of the affected MLG sliding tubes (both retained affected parts and additional affected parts) for cracks, and replacement if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also adds airplanes to the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
2014-03-13: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by three reports of cracking in the rear pressure bulkhead (RPBH) web. This AD requires inspecting the RPBH web for cracking, and repairing if necessary. We are issuing this AD to detect and correct cracking of the RPBH web, which could result in in-flight decompression of the airplane and possible injury to the occupants.
99-20-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and Mark 0100 series airplanes, that currently requires revising the Airplane Flight Manual to provide the flightcrew with instructions not to arm the liftdumper system prior to commanding the landing gear to extend. This amendment requires modification of the grounds of the shielding of the wheelspeed sensor wiring of the main landing gear (MLG) and installation of new electrical grounds for the wheelspeed sensor channel of the anti-skid control box of the MLG. 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 electromagnetic interference generated by electrical wiring that runs parallel to the wheelspeed sensor wiring, which could result in inadvertent deployment of the liftdumpers during approach for landing or reduced brake pressure during low speed taxiing, and consequent reduced controllability and performance of the airplane.
87-18-01: 87-18-01 FOKKER B.V.: Amendment 39-5719. Applies to Model F28 airplanes certificated in any category, serial numbers 11003 through 11195, 11991, and 11992. Compliance required as indicated, unless previously accomplished. To prevent uncommanded movement of the horizontal stabilizer as a result of fatigue failure of certain bolts within the horizontal stabilizer control unit, accomplish the following within one year after the effective date of this AD: A. Replace the horizontal stabilizer control unit in accordance with the Accomplishment Instructions in Fokker Service Bulletin No. F28/F27-168, Revision 1, dated June 30, 1986. 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. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base forthe 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 Fokker Aircraft, 1199 North Fairfax Street, Alexandria, Virginia 22314. 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 October 7, 1987.
2014-04-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of chaffing, arcing, and burning damage to the control cabin overhead wiring and ducting with smoke and fire caused by metal clamps installed on certain hoses. This AD requires inspecting for the presence of metal clamps, replacing metal clamps installed on the hoses to the air conditioning temperature sensor, gasper air outlet, and diffuser on the left side of the control cabin with plastic tie straps, and inspecting for and repairing damaged wire bundles. We are issuing this AD to prevent damage to wire bundles, which could cause electrical arcing that could result in a fire or smoke in the control cabin of the airplane.
91-23-13: 91-23-13 GENERAL ELECTRIC COMPANY: Amendment No. 39-8082. Docket No. 91- ANE-38. Applicability: General Electric Company (GE) CF6-50 series and CF6-80A series turbofan engines, installed on, but not limited to, Airbus A300 and A310, Boeing 747 and 767, and McDonnell Douglas DC10-15 and DC10-30 aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent an uncontained engine failure and damage to the aircraft, accomplish the following: (a) Within 30 days after the effective date of this AD, remove from service stage 1 fan disks identified by the following part number (P/N) and serial number (S/N): ENGINE MODEL PART NUMBER SERIAL NUMBER CF6-50 9253M66P02 MPON2919 9253M66P02 MPON2920 9253M66P02 MPON2921 9253M66P02 MPON2922 CF6-80A 9319M28P03 MPON4290 1327M57P02 MPON4291 9319M28P02 MPON4292 9319M28P03 MPON7740 9319M28P03 MPON7742 9319M28P03 MPON8452 9319M28P03 MPON8453 Prior to returning affected engines to service replace with a serviceable part. (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 Inspector (maintenance, avionics, or operations, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. This amendment (39-8082, AD 91-23-13) becomes effective on November 22, 1991.
99-20-04: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT9D-7R4 series turbofan engines, that requires an initial and repetitive inspections of certain High Pressure Turbine (HPT) stage 1 and stage 2 disks utilizing an improved ultrasonic inspection method performed at an approved facility when the disks are exposed during a shop visit, and if a crack indicating a subsurface anomaly is found, removal from service and replacement with a serviceable part. This amendment is prompted by the results of a stage 1 HPT disk fracture investigation which has identified a population of HPT stage 1 and 2 disks that may have subsurface anomalies formed during the forging process. The actions specified by this AD are intended to prevent an HPC disk fracture, which could result in an uncontained engine failure, damage to the airplane, and an in-flight engine shutdown. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of October 29, 1999.
99-20-02: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that currently requires Airplane Flight Manual (AFM) and maintenance program revisions, modifications, and repetitive checks associated with ensuring the integrity of the thrust reverser system. This amendment continues to require the modifications and repetitive checks, and adds an AFM revision, repetitive operational tests, and other modifications related to the thrust reverser system. The new modifications terminate the repetitive operational checks and tests. This amendment is prompted by results of a review, which indicated that a potential latent failure of the secondary lock actuator switch 1 of the thrust reverser system in the open position may occur, in addition to the potential failure of the secondary lock relay 1 in the energized position. The actions specified by this AD are intended to ensure protection against inadvertent deployment of the thrust reversers during flight, which could result in reduced controllability of the airplane.
86-16-03: 86-16-03 ALLISON GAS TURBINE DIVISION, GENERAL MOTORS CORP. (ALLISON, formerly DETROIT DIESEL ALLISON): Amendment 39-5366. Applies to Allison Model 250-C28B and -C28C engines installed in aircraft certificated in any category. The following engine models and turbine serial numbers are affected: ENGINE MODEL ENGINE SERIAL NUMBER TURBINE SERIAL NUMBER 250-C28B CAE 860011 thru 860787 CAT 70011 thru 70804 250-C28C CAE 280001 thru 280097 CAT 28001 thru 28098 EXCEPT: Existing Model 250-C28B and -C28C engines which have incorporated Allison Commercial Engine Alert Bulletin CEB-A-72-2138 dated May 15, 1986, or FAA approved equivalent. Compliance is required as indicated unless already accomplished. To prevent possible internal oil fires that can cause cracks under the rim of the first stage turbine wheel which can progress to an on-speed failure/uncontained failure, accomplish the following: (a) Maintain a record of oil consumed and flight hours, beginningon the effective date of this AD, until compliance with Paragraph (c). (b) Troubleshoot and repair, before further flight, any engine that exhibits any of the following conditions: (1) High oil consumption (1 quart in 5 hours, .05 gallons per hour, or .19 liters per hour) or significant step change of 100 percent or greater in oil consumption. (2) Excessive smoking on deceleration and/or shutdown with or without associated high oil consumption or significant increase in oil consumption. NOTES: (1) The checks required by Paragraph (a), (b)(1), and (b)(2) of this AD may be performed by the pilot and must be recorded in accordance with FAR 43.9. (2) Allison Model 250-C28 Series Operations and Maintenance/Overhaul Manual addresses troubleshooting and repairs. (c) Install Number 8 Bearing Scavenge Line Air/Oil Centrifugal Separator Assembly, P/N 23034772, in accordance with Allison Commercial Engine Alert Bulletin CEB-A-72-2138 dated May 15, 1986, or FAA approved equivalent, not later than January 31, 1987. NOTE: Installation of the Number 8 Bearing Scavenge Line Air/Oil Centrifugal Separator Assembly, P/N 23034772, does not relieve the operator of proper monitoring of oil consumption, changes in oil consumption or smoking during operation as described in the Model 250-C28 Series Engine Operations and Maintenance Manual. 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, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. 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 CEB-A-72-2138 dated May 15, 1986, 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, IN 46206- 0420. This document also may be examined at the Office of Regional Counsel, FAA, ATTN: Rules Docket No. 86-ANE-28, 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 August 13, 1986.
2014-03-20: We are adopting a new airworthiness directive (AD) for certain Piaggio Aero Industries S.P.A Model P-180 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as insufficient clearance between one of the horizontal stabilizer end ribs and the corresponding elevator horn. We are issuing this AD to require actions to address the unsafe condition on these products.
2014-03-08: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report that an investigation showed that when a certain combination of a target/proximity sensor serial number is installed on a flap interconnecting strut, a ``target FAR'' signal cannot be detected when it reaches the mechanical end stop of the interconnecting strut. This AD requires an inspection to determine the part number of the interconnecting struts installed on the wings, identifying the part number and the serial number of the associated target and proximity sensor if applicable, and replacing or re-identifying the flap interconnecting strut if applicable. We are issuing this AD to detect and correct a latent failure of the flap down drive disconnection due to an already-failed interconnecting strut sensor, which could result in asymmetric flap panel movement and consequent loss of control of the airplane.