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93-22-08: 93-22-08 JETSTREAM AIRCRAFT, LIMITED: Amendment 39-8732. Docket 93-NM-176-AD. ` Applicability: All Model 4101 airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent high current arcing and overheating of certain earth post assemblies and their associated earth (ground) wires, thus creating an in-flight fire hazard, accomplish the following: (a) Within 25 hours time-in-service after the effective date of this AD, conduct a visual and hands-on inspection to detect discrepancies (i.e., overheating, looseness, etc.) of earth post EP2 (left) and earth post EP4 (right) and their attached earth cables, in accordance with the Accomplishment Instructions of Jetstream Series 4100 Alert Service Bulletin J41-A24-012, Revision 1, dated September 13, 1993. (1) If no discrepancy is detected, no further action is required. (2) If any discrepancy is detected, prior to further flight, replace the discrepant earth post with a new earth post and earth cables in accordance with paragraph B. of the Accomplishment Instructions of Jetstream Series 4100 Alert Service Bulletin J41-A24-012, Revision 1, dated September 13, 1993. (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 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. (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 inspections and replacement shall be done in accordance with Jetstream Series 4100 Alert Service Bulletin J41-A24-012, Revision 1, dated September 13, 1993, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1, 3, 6 1 September 13, 1993 2, 4-5, 7, Original September 8, 1993 8, 9 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 Jetstream Aircraft, Inc., P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. 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 December 3, 1993.
77-15-04: 77-15-04 ENSTROM: Amendment 39-2973. Applies to Enstrom Models F28C and 280C helicopters with wide chord (4.4 inch) tail rotor blades certificated in all categories. Before further flight perform a dye penetrant inspection around the circular hub including the arm base of the pitch link retainer assembly P/N 28-16320 unless already accomplished in the last ten hours time in service. Within ten (10) hours time in service after the receipt of this airmail letter, unless already accomplished, replace the wide chord tail rotor pitch link assembly P/N 28- 16320 and two (2) guide bolts P/N 28-16307 with a new wide chord tail rotor pitch link retainer assembly P/N 28-16325 and two (2) guide bolts P/N 28-16324. Enstrom Service Directive Bulletin Number 0040 pertains to this same subject. This amendment is effective July 26, 1977, and was effective immediately for all recipients of airmail letters dated June 15, 1977 which contained this amendment.
2004-13-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200B, and -200F series airplanes. This action requires initial and repetitive inspections to find discrepancies in the upper and lower skins of the fuselage lap joints, and repair if necessary. This action is necessary to find and fix such discrepancies, which could result in sudden fracture and failure of a lap joint and rapid in-flight decompression of the airplane fuselage. This action is intended to address the identified unsafe condition.
76-13-04: 76-13-04 MCDONNELL DOUGLAS: Amendment 39-2652. Applies to Douglas Model DC-10-10 and -30 series airplanes, certificated in all categories, incorporating lower galleys. \n\n\tCompliance required within the next 3000 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo provide better access to the portable oxygen units in the lower galley, relocate the two portable oxygen units originally installed outboard of the forward escape ladder in the lower galley to the port side of the forward bulkhead and adjacent to the attendant seats. Additional installations and/or other locations may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tSpecial flight permits may be issued per FAR's 27.197 and 21.199 to operate airplanes to a base for the accomplishment of this AD. \n\n\tThis amendment becomes effective August 3, 1976.
95-09-06: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters, that requires installing a protective mechanical fuel valve switch guard on the fuel valve switch. This amendment is prompted by reports of airmen inadvertently placing the fuel valve switch to the "OFF" position. The actions specified by this AD are intended to prevent the fuel valve switch from being inadvertently placed in the "OFF" position, which could result in an engine failure and a subsequent power-off landing.
93-20-06: 93-20-06 AYRES CORPORATION: Amendment 39-8714; Docket No. 93-CE-31-AD. Applicability: The following model and serial number airplanes, certificated in any category: Models Serial Numbers S2D all serial numbers S2R 5000 through 5099, 1380R, and 1416R through 2582R S2R-R1340 R1340-001 through R1340-028 (with or without DC suffix) S2R-R3S R3S-001 through R3S-011 (with or without DC suffix) S2R-R1820 R1820-001 through R1820-035 (with or without DC suffix) S2R-T11 T11-001 through T11-005 (with or without DC suffix) S2R-T15 T15-001 through T15-029 (with or without DC suffix); and T27-001 through T27-029 (with or without DC suffix) S2R-T34 6000 through 6049, T34-001 through T34-143, T34-145, T34-147 through T34-167, T34-170, T34-171, and T34-180 (with or without DC suffix); and T41-001 through T41-143, T41-145, T41-147 through T41-167, T41-170, T41-171, and T41-180 (with or without DC suffix) S2R-T45 T45-001 (with or without DC suffix) Compliance: Required as indicated, unless already accomplished. NOTE 1: The compliance times specified in this AD take precedence over those referenced in Ayres Service Bulletin (SB) No. SB-AG-33, dated February 24, 1993. To prevent structural damage to the wing caused by damaged aluminum outboard wing huckbolts, which could result in loss of control of the airplane, accomplish the following: (a) Within the next 50 hours time-in-service after the effective date of this AD, inspect the existing aluminum outboard wing huckbolts for cracks, shearing, or fatigue in accordance with the ACCOMPLISHMENT INSTRUCTIONS: I. Inspection, section of Ayres SB No. SB-AG-33, dated February 24, 1993. (1) If sheared, cracked, or fatigued aluminum outboard wing huckbolts are found, prior to further flight, replace the last 13 vertical rows of aluminum huckbolts with NAS 1103 steel bolts or with steel huckbolts in accordance with the ACCOMPLISHMENT INSTRUCTIONS: II. Repair, section of Ayres SB No. SB-AG-33, dated February 24, 1993. (2) If no cracked, sheared, or fatigued huckbolts are found, reinspect at intervals not to exceed 100 hours TIS. Accomplish no more than five 100-hour inspection repetitions before replacing the huckbolts as required by paragraph (b) of this AD. NOTE 2: The FAA established the compliance times of the initial inspection and the repetitive inspections to coincide with the replacement compliance time specified in paragraph (b) of this AD. (b) Within the next 650 hours TIS after the effective date of this AD, unless already accomplished in accordance with paragraph (a)(1) of this AD, replace the last 13 vertical rows of aluminum huckbolts with NAS 1103 steel bolts or with steel huckbolts in accordance with the ACCOMPLISHMENT INSTRUCTIONS: II. Repair, section of Ayres SB No. SB-AG-33, dated February 24, 1993. NOTE 3: The FAA established the replacement compliance time by estimating airplane operation rates in order to allow the operator the opportunity to accomplish the action during the next annual maintenance inspection. (c) Replacing the huckbolts as specified in paragraph (b) of this AD eliminates the inspection requirement of this AD and may be accomplished prior to 650 hours TIS. (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) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (f) The inspection and replacement required by this AD shall be done in accordance with Ayres Service Bulletin No. SB-AG-33, dated February 24, 1993. 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 the Ayres Corporation, P.O. Box 3090, Albany, Georgia 31708. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment (39-8714) becomes effective on December 3, 1993.
2009-24-04: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) AE 3007A1/1, AE 3007A1/3, AE 3007A1, AE 3007A1E, AE 3007A1P, AE 3007A3, AE 3007C, and AE 3007C1 turbofan engines with a fan spinner part number (P/N) 23070964 or P/N 23078783, installed. This AD requires replacement of the fan spinner. This AD results from a report of a fan spinner releasing from an AE 3007A turbofan engine, during flight. We are issuing this AD to prevent the fan spinner from releasing, which could result in injury, damage to the engine, and damage to the airplane.
92-27-01: 92-27-01 AEROSPATIALE: Amendment 39-8434. Docket No. 92-NM-147-AD. Applicability: All Model ATR42 and ATR72 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent increased risk of injury to the passengers and crew members in the event of a fire within the airplane cabin, accomplish the following: (a) For Model ATR42 series airplanes: Within 2 years after the effective date of this AD, remove the door linings and perform a general visual inspection to determine the date of their manufacture, in accordance with Aerospatiale Service Bulletin ATR42-25-0084, dated April 10, 1992. (1) If the door linings were manufactured prior to January 15, 1990, prior to further flight, replace them with linings manufactured after January 15, 1990, in accordance with Aerospatiale Service Bulletin ATR42-25-0075, dated September 4, 1991. (2) If the door linings were manufactured on or after January 15, 1990, reinstall the linings. No further action is required by this AD. (b) For Model ATR72 series airplanes: Within 2 years after the effective date of this AD, remove the door linings and door posts and perform a general visual inspection to determine the date of their manufacture, in accordance with Aerospatiale Service Bulletin ATR72-25-1025, Revision 1, dated May 18, 1992. (1) If the door linings or door posts were manufactured prior to January 15, 1990, prior to further flight, replace them with linings or posts manufactured after January 15, 1990, in accordance with ATR72-25-1020, dated September 4, 1991. (2) If the door linings or door posts were manufactured on or after January 15, 1990, reinstall the linings or posts. No further action is required by 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 inspections and replacements shall be done in accordance with Aerospatiale Service Bulletin ATR42-25-0084, dated April 10, 1992; Aerospatiale Service Bulletin ATR42-25- 0075, dated September 4, 1991; Aerospatiale Service Bulletin ATR72-25-1025, Revision 1, dated May 18, 1992; or Aerospatiale Service Bulletin ATR72-25-1020, dated September 4, 1991; as applicable. Aerospatiale Service Bulletin ATR72-25-1025, Revision 1, dated May 18, 1992, contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1 1 May 18, 1992 2-9 Original April 10, 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, 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. (e) This amendment becomes effective on January 22, 1993.
91-16-07: 91-16-07 BRITISH AEROSPACE: Amendment 39-7097. Docket No. 91-NM-79-AD. Applicability: Model ATP series airplanes, equipped with Smiths Industries Altimeter Repeater Units, Part Number 1205AM1, certificated in any category. Compliance: Required within 120 days after the effective date of this AD, unless previously accomplished. To ensure the pilot receives accurate altitude data, accomplish the following: A. Install a hardened knobshaft, Part Number AM10588, in place of Part Number AM10454, and remount the microswitch (Smiths Industries Modification No. 02), in accordance with British Aerospace Service Bulletin ATP-34-40, dated October 20, 1990. NOTE: The British Aerospace service bulletin references Smiths Industries Service Bulletin 1205AM-34-756 for additional instructions. B. An alternative method 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, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may 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. D. The modification requirement shall be done in accordance with British Aerospace Service Bulletin ATP-34-40, dated October 20, 1990. 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, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-7097, AD 91-16-07) becomes effective on September 11, 1991.
92-19-12: 92-19-12 LEARJET (FORMERLY GATES LEARJET): Amendment 39-8370. Docket No. 92-NM-111-AD. Applicability: Model 23, 24, 25, 28, 29, 31, 35, and 36 series airplanes, as listed in Learjet Airplane Modification Kit No. AMK 90-5, dated October 11, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent electrical arcing and an in-flight fire, accomplish the following: (a) Within 30 days after the effective date of this AD, modify the crew oxygen plumbing and map light wires, in accordance with Learjet Airplane Modification Kit AMK No. 90-5, dated October 11, 1991. (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, Wichita Aircraft Certification Office (ACO), ACE-115W, FAA, Small 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, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita 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 modification shall be done in accordance with Learjet Airplane Modification Kit AMK No. 90-5, dated October 11, 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 Learjet Corporation, Customer Services, P.O. Box 7707, Wichita, Kansas 67277-7707. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on November 17, 1992.