Results
98-15-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111 and -211 series airplanes. This action requires repetitive inspections to detect fatigue cracking of the frames of the sliding windows in the cockpit, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct fatigue cracking of the frames of the sliding windows in the cockpit, which could result in reduced structural integrity of the pressure vessel of the fuselage of the airplane.
2009-26-02: We are adopting a new airworthiness directive (AD) for the products listed above. 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 describes the unsafe condition as: It has been found the occurrence of engine anti-ice system valve failure, where the valve spring seat has broken and obstructed the anti-ice system venturi tube. * * * Therefore, should the aircraft encounter icing conditions, ice may accrete in the engine inlet lip and be ingested through the air inlet, resulting in possible engine damage and flame-out. We are issuing this AD to require actions to correct the unsafe condition on these products.
97-19-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that currently requires revising the Limitations Section of the Airplane Flight Manual (AFM) to provide the flight crew with procedures to check the travel range of the aileron. That AD also requires inspection for damage of the shear pins of the aileron flutter damper and aileron hinge fittings, and various follow-on actions. This amendment adds a requirement for accomplishment of an installation that eliminates the need for the AFM revision. This amendment also adds airplanes to the applicability of the existing AD. This amendment is prompted by reports of failure of shear pins in the aileron flutter damper. The actions specified by this AD are intended to prevent damage to the aileron hinge fittings due to failed shear pins, and consequent reduced controllability of the airplane.
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.
93-14-07: 93-14-07 AEROSPATIALE: Amendment 39-8631. Docket 93-NM-06-AD. Applicability: Model ATR72-100 and -200 series airplanes; on which either Modification 03616, as described in Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992, or Modification 03584 have not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of structural strength of the floor beam and pressure plate, or loss of cabin pressurization, accomplish the following: (a) Prior to the accumulation of 1,000 total flight cycles, or within the next 30 days after the effective date of this AD, whichever occurs later, perform a detailed visual inspection to detect cracks of the floor beam at frame 26 of the fuselage in the buttock line 0 area, in accordance with Aerospatiale Service Bulletin ATR72-53-1026, Revision 1, dated January 22, 1993. (1) If no crack is found, accomplish either paragraph (a)(1)(i) or (a)(1)(ii) of this AD: (i) Thereafter, at intervals not to exceed 1,000 flight cycles, repeat the detailed visual inspection. (ii) Within the next 1,000 flight cycles, install Modification 03616 in accordance with Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992. No further action is required by this AD. (2) If a single crack is found that is less than 65 millimeters (mm) in length, accomplish either paragraph (a)(2)(i) or (a)(2)(ii) of this AD. (i) Thereafter, at intervals not to exceed 750 flight cycles, repeat the detailed visual inspection. (ii) Within the next 750 flight cycles after crack discovery, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (3) If a single crack is found that is equal to or greater than 65 mm but less than 80 mm in length: Within the next 250 flight cycles after crack discovery, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (4) If a single crack is found that is equal to or greater than 80 mm in length: Prior to further flight, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (5) If two or more cracks are found: Prior to further flight, repair the cracks in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (b) Prior to the accumulation of 1,000 total flight cycles, or within the next 30 days after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) inspection of the pressure plate forward and aft of the floor beam at frame 26 of the fuselage at buttock line 0, in accordance with Aerospatiale Service Bulletin ATR72-53-1026, Revision 1, dated January 22, 1993. (1) If no crack is found, accomplish either paragraph (b)(1)(i) or (b)(1)(ii) of this AD: (i) Thereafter, at intervals not to exceed 1,000 flight cycles, repeat the HFEC inspection. (ii) Within the next 1,000 flight cycles, install Modification 03616 in accordance with Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992. No further action is required by this AD. (2) If a single crack is found that is less than 65 millimeters (mm) in length, accomplish either paragraph (b)(2)(i) or (b)(2)(ii) of this AD: (i) Thereafter, at intervals not to exceed 500 flight cycles, repeat the HFEC inspection. (ii) Within the next 500 flight cycles after crack discovery, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (3) If a single crack is found that is equal to or greater than 65 mm but less than 80 mm in length: Withinthe next 250 flight cycles after crack discovery, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (4) If a single crack is found that is equal to or greater than 80 mm in length: Prior to further flight, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (5) If two or more cracks are found: Prior to further flight, repair the cracks in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (c) Within 6 months after the effective date of this AD, if no crack is present, install Modification 03616 in accordance with Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992; or, if any crack is present, repair in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. (d) Installation of Modification 03616 in accordance with Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992; or repair in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993; constitutes terminating action for the repetitive detailed visual inspections of the floor beam and repetitive HFEC inspections of the pressure plate required by this AD. (e) 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. (f) 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. (g) The inspection shall be done in accordance with Aerospatiale Service Bulletin ATR72-53-1026, Revision 1, dated January 22, 1993. The installation shall be done in accordance with Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992. The repair shall be done in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 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 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. (h) This amendment becomes effective on September 10, 1993.
93-15-05: 93-15-05 AIRBUS INDUSTRIE: Amendment 39-8651. Docket 93-NM-117-AD. Applicability: Model A320 series airplanes on which Airbus Industrie Modification 20856 or Airbus Industrie Service Bulletin A320-32-1090 has been accomplished, and on which Airbus Industrie Modification 23597 or Airbus Industrie Service Bulletin A320-32-1114 has not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced braking performance, accomplish the following: (a) Within 30 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) by inserting a copy of Airbus Industrie A320 Flight Manual Temporary Revision 9.99.99/89, Issue 2, dated December 16, 1992, in the AFM. (b) Accomplishment of Airbus Industrie Modification 23597 or Airbus Industrie Service Bulletin A320-32-1114 and replacement of Airbus Industrie A320 Flight Manual Temporary Revision 9.99.99/89, Issue 2, dated December 16, 1992, with Airbus Industrie A320 Flight Manual Temporary Revision 9.99.99/89, Issue 3, dated February 8, 1993, in the AFM constitutes terminating action for the requirements of paragraph (a) 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 AFM revision shall be accomplished in accordance with Airbus Industrie A320 Flight Manual Temporary Revision 9.99.99/89, Issue 2, dated December 16, 1992, which contains the following list of effective pages: Page Number Issue Level Shown on Page Date Shown on Page 1 2 December 16, 1992 2 Original November 3, 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 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 August 18, 1993.
47-51-14: 47-51-14 SIKORSKY: Applies to Models YR-6A, R-6A, HOS-1 Helicopters. Compliance required at each removal and replacement of the power takeoff assembly. In order to prevent failure of the pinion and ring gears in the main gearbox due to improper installation of the power takeoff assembly, the following teardown, inspection, and assembly procedure should be followed: (a) Disconnect and remove the front end of the intermediate drive shaft. (b) Remove the cotter pin and nut in the center of the spline coupling, P/N S-635104, and remove the spline coupling with attached brake disc. (c) Check the backlash in the power takeoff gears. This should be 0.003 to 0.005 inch between the ring gear and pinion. (d) Remove the five retaining nuts and washers securing the power takeoff to the main gearbox lower housing. (e) Using a fiber mallet, for starting, remove the power takeoff. CAUTION: Do not use a screwdriver or pry bar on the mating surfaces, as the slightest deformation of the surfaces may cause gear failure. (f) Inspect the shims, P/N S-635117, and gasket, P/N S-635115, for dents and tears. Only shims and gaskets in perfect condition should be considered serviceable. Also, the mating surfaces of the housings should be free from rough spots or tool deformations. (g) With a micrometer, measure the total thickness of the shim. If it is necessary to replace a shim, and the backlash was within limits, the replacement shim must have the same total thickness as the parts removed. (h) Lightly coat with Prussian blue the teeth of the power takeoff pinion. (i) Place gasket P/N S-635115 in gasket recess. (j) Replace the shims over the five studs in the lower case of the main gearbox, install the power takeoff housing assembly, and secure the five washers and nuts. (k) Check the backlash between the ring gear and pinion, which must be between 0.003 to 0.005 inch. (l) After the power takeoff has been fastened securely in place, the gearbox must be operated by hand by turning the end of the pinion shaft protruding from the power takeoff. After a few revolutions, remove the power takeoff and check the tooth pattern. The correct tooth pattern is shown in Figure 5. The necessary adjustment for proper tooth pattern and backlash should be accomplished by shimmying with power takeoff housing shims. Shims are to provide adjustments for both mounting distance of ring gear and pinion and also tooth pattern. (m) When the proper tooth pattern and backlash have been obtained, install the power takeoff and securely tighten retaining nuts. (n) Replace the spline coupling with brake disc attached and secure with washer, nut, and cotter pin. (o) Reassemble the front end of the intermediate drive shaft. (Similar instructions are contained in AAF Technical Order No. 01-230 of HC-16, dated March 6, 1946, and in Bureau of Aeronautics Aircraft Bulletin No. 6 dated March 28, 1947.)
86-01-07: 86-01-07 HAMILTON STANDARD: Amendment 39-5209. Applies to Hamilton Standard model 54H60-77, -81, -123, -125, -131, and -133 propellers with propeller control S/N 850901 or lower installed on, but not limited to, CV580, L188 and Guppy aircraft. Compliance is required within the next 30 days after the effective date of this AD, unless already accomplished. To prevent loss of aircraft control and possible loss of aircraft, accomplish the following: (a) Within the next 30 days after the effective date of this AD, conduct a functional check of the propeller valve housing cover input gear in accordance with Hamilton Standard 54H60 ASB No. 61-A119, Paragraph 2.A dated December 10, 1985, or FAA-approved equivalent. (1) If the application of less than 36 pounds of load causes slippage of the input lever, remove the valve housing cover assembly prior to further flight. (2) If 36 to 38 pounds can be maintained without slippage of the input lever, mark the valve housing cover in accordance with Paragraph 2.D.(1) and return to service. (b) At the next component maintenance/propeller overhaul after completing the above functional check or by January 15, 1988, whichever occurs sooner, inspect the valve housing cover in accordance with Paragraphs 2.B and 2.C of 54H60 ASB No. 61-A119. Remove from service all input gears with change letter "G" indicated and replace with a serviceable gear. Mark the valve housing cover in accordance with Paragraph 2.D.(2). 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 and Propeller Standards Staff, ANE-110, Federal Aviation Administration, 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 and Propeller Standards Staff may adjust the compliance time specified in this AD. Hamilton Standard 54H60 ASB No. 61-A119, dated December 10, 1985, 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 Hamilton Standard, Division of United Technologies Corporation, Windsor Locks, Connecticut 06096. This document also may be examined at the Office of the Regional Counsel, Attn: Rules Docket 85-ANE-48, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on January 17, 1986.
86-14-06: 86-14-06 BRITISH AEROSPACE: Amendment 39-5351. Applies to Model BAe 125- 800A series airplanes with manufacturer serial numbers listed in British Aerospace 125 Service Bulletin 24-248-(3024), dated March 8, 1985, certificated in any category. To prevent complete loss of power to the Electronic Flight Instrument System (EFIS), accomplish the following within the next 60 days after the effective date of this AD, unless previously accomplished: A. Perform the following actions as applicable: 1. For airplanes with manufacturer serial numbers 258003 and 258010, and for airplanes which have utilized power supplies HN1/HP1, the existing heat-sink must be replaced with a new sub-assembly, as described in Part A of the accomplishment instructions of British Aerospace Service Bulletin 24-248-(3024), dated March 8, 1985; or 2. If power supplies HN1/HP1 have not been utilized, the existing heat-sink assembly and associated power supply cabling from ground supply contactor "E"on panel GA must be replaced in accordance with Part B of the accomplishment instructions of British Aerospace Service Bulletin 24-248-(3024), dated March 8, 1985. 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 for the accomplishment of inspections and/or 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 British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041. 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 August 8, 1986.
75-22-02: 75-22-02 AVCO LYCOMING: Amendment 39-2385. Applies to all Avco Lycoming T53 series engines. To prevent secondary failure of the N2 accessory drive shaft, as a result of binding of the torquemeter boost pump drive shaft, remove torquemeter boost pump, Part Number 1-300-221-01 or Part Number 1-300-221- 02, and replace with Part Number 1-300-221-03 or Part Number 1-300-221-04 within 200 hours time in service after the effective date of this AD. NOTE: Avco Lycoming Service Bulletin Number 0031 pertains to this subject. This amendment becomes effective October 29, 1975.
91-14-15: 91-14-15 HOFFMANN AIRCRAFT, LTD.: Amendment 39-7056. Docket No. 90-CE-51- AD. Applicability: Model H-36 Dimona motor gliders (serial numbers 3501 through 36143) that were supplied or equipped with a fuel tank made of glass fiber reinforced plastic (GFRP) or fiber reinforced plastic (FRP), certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To avoid engine shutdown caused by solid or rubber-like gelcoat fuel deposits, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) or within the next 6 calendar months, whichever occurs first, accomplish the following: (1) Statically ground the glider and the fuel system. (2) Empty the fuel tank through a drainer, ventilate the tank, and then remove the tank. (3) Remove the gasoline filter and inspect the filter and the fuel lines for solid or rubber-like deposits. Remove any solid or rubber-like deposits and thoroughly clean the filter. (4) Replace the GFRP or FRP fuel tank with an aluminum tank, Part Number 820.5.12 S3a, and reinstall the gasoline filter and reconnect the fuel lines. (5) Using pen and ink, correct the glider weight and balance data sheet as follows: (i) Decrease the empty weight by 2.2 pounds (1kg). (ii) Show a forward shift of 0.06 inches (1.5mm) of the empty weight center of gravity value. (6) Using pen and ink, change the Maintenance and Inspection checklist, page 36 of the maintenance manual, by adding the following notations: (i) "14. Check fuel lines and tank assembly for security and leaks." (ii) Enter the symbol "0" in columns marked "100 hours" and "500 hours". (b) If the aluminum tank required by paragraph (a)(4) of this AD has been ordered, but is not available, within the next 50 hours TIS or 6 calendar months after the effective date of this AD, whichever occurs first, and thereafter at intervals not toexceed 100 hours TIS or 12 calendar months, whichever occurs first, accomplish the following interim actions: (1) Statically ground the glider and the fuel system. (2) Empty the fuel tank through a drainer, ventilate the tank, and then remove the tank. (3) Remove the gasoline filter and inspect the filter and the fuel lines for solid or rubber-like deposits. Remove any solid or rubber-like deposits and thoroughly clean the filter. (4) Remove the finger filter and inspect it for solid or gelatinous deposits, remove any solid or gelatinous deposits, and thoroughly clean the filter. (5) Perform the following inspections on the inner side of the fuel tank: (i) Inspect for deposits through the filler hole with a mirror and light. (ii) Inspect for softened spots in the gelcoat with a wood spatula. (A) If no deposits or soft spots are found in the fuel tank as a result of these inspections, the glider may be operated until the fuel tank specified in paragraph (a)(4) of this AD becomes available. (B) If any deposits or soft spots are found in the tank as a result of these inspections, prior to further flight, replace the fuel tank in accordance with the instructions of paragraph (a) of this AD. (c) 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, Brussels Aircraft Certification Office, 15 Rue de la Loi, B-1040 Brussels Belgium, c/o American Embassy APO, New York, New York 09667. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (d) Information that is related to this AD may be obtained from the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri. This amendment (39-7056, AD 91-14-15) becomes effective on August 12, 1991.
95-11-11 R1: This amendment clarifies information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas DC-10 and KC-10 series airplanes, that currently requires repetitive eddy current inspections to detect fatigue cracking of the pylon aft bulkhead flange, upper pylon box web, fitting radius, and adjacent tangent areas; and repair, if necessary. The actions specified in that AD are intended to prevent failure of the wing pylon aft bulkhead due to fatigue cracking, which could lead to separation of the engine and pylon from the airplane. This amendment clarifies the requirements of the current AD by specifying the type of initial and repetitive inspections that must be conducted. This amendment is prompted by communications received from affected operators that the current requirements of the AD are unclear.
2021-22-17: The FAA is adopting a new airworthiness directive (AD) for all Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. This AD was prompted by a report of cracking in certain components on left and right sides of the aft wing-to-body fairing (WTBF) structure near the tie-rod attachment at a certain fuselage station; this cracking likely resulted from excessive tie-rod preload. This AD requires inspecting the aft WTBF structure for any cracking or damage, adjusting the load on the two tie-rods at a certain fuselage station, and repair if necessary, as specified in two Transport Canada Civil Aviation (TCCA) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2009-21-08: We are adopting a new airworthiness directive (AD) for the products listed above. 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: Some cases of uncommanded steering action were observed, while the steering system was switched off. A leakage in the Steering Select/Bypass Valve, installed in the Steering Manifold, when closed, is suspected to have caused the uncommanded steering. If left uncorrected, this condition could lead to a potentially dangerous veer along the runway; in fact, according to the Aircraft Flight Manual limitations, the steering system must be in `off' position during landing and takeoff (in this case when airspeed is higher than 60 knots). We are issuing this AD to require actions to correct the unsafe condition on these products.
94-20-03: This amendment supersedes an existing airworthiness directive (AD) applicable to Bell Helicopter Textron, Inc. (BHTI) Model 206A, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 helicopters, that currently requires an inspection of the main rotor hub trunnion (trunnion) for a mislocated master spline and replacement of any trunnion that has a mislocated master spline. This amendment is prompted by a report that certain main rotor hub trunnions (trunnions) were manufactured with a mislocated master spline. The actions specified by this AD are intended to identify and require replacement of any trunnion with a mislocated master spline to prevent pitch link misalignment, altered cyclic stick control position, loss of the main rotor system, and subsequent loss of control of the helicopter.
91-22-07: 91-22-07 MCDONNELL DOUGLAS: Amendment 39-8067. Docket No. 91-NM-88-AD. Supersedes AD 91-03-07, Amendment 39-6869. \n\n\tApplicability: Model DC-9-10, -20, -30, -40, and -50 series and C-9 (Military) series airplanes; fitted with left (LH) or right (RH) main landing gear (MLG) outboard door with a wing-mounted aluminum hinge half (Group I) or titanium hinge half (Group II); certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the loss of the LH or RH MLG outboard door, accomplish the following: \n\n\t(a)\tFor Group I airplanes: Within 30 days after February 11, 1991 (the effective date of Amendment 39-6869, AD 91-03-07), and thereafter at intervals not to exceed one year, accomplish the following in accordance with McDonnell Douglas Alert Service Bulletin A32-244, dated November 20, 1990, for both the LH and RH MLG outboard door assemblies: \n\n\t\t(1)\tInspect the MLG door for delamination; and \n\n\t\t(2)\tInspect the MLG door linkages and their attachments for corrosion, pitting, wear, and general conditions; and \n\n\t\t(3)\tInspect the MLG door hinge lobes on both the wing-mounted hinge half and door-mounted hinge half for cracks and corrosion; and \n\n\t\t(4)\tInspect the hinge halves on articulating doors for cracks and corrosion. \n\n\t(b)\tFor Group II airplanes: Within 50 days after the effective date of this AD, and thereafter at intervals not to exceed one year, accomplish the following in accordance with McDonnell Douglas Alert Service Bulletin A32-244, dated November 20, 1990, for both the LH and RH MLG outboard door assemblies: \n\n\t\t(1)\tInspect the MLG door for delamination; and \n\n\t\t(2)\tInspect the MLG door linkages and their attachments for corrosion, pitting, wear, and general conditions; and \n\n\t\t(3)\tInspect the MLG door hinge lobes on both the wing-mounted hinge half and door-mounted hinge half for cracks and corrosion; and \n\n\t\t(4)\tInspect the hinge halves on articulating doors for cracksand corrosion. \n\n\t(c)\tFor Group I and II airplanes: Within 18 months after the effective date of this AD, measure the aluminum hinge lobes, if bushed, for minimum wall thickness of .055 inch or greater, in accordance with McDonnell Douglas Alert Service Bulletin A32-244, dated November 20, 1990. \n\n\t(d)\tIf discrepancies are found as a result of the inspections required by paragraph (a), (b), or (c) of this AD, prior to further flight, repair in a manner approved by the Manager of the Los Angeles Aircraft Certification Office (ACO). \n\n\t(e)\tAn 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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\t(f)\tSpecial flight permitsmay 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\t(g)\tThe inspection, replacement, and repair requirements shall be done in accordance with McDonnell Douglas Alert Service Bulletin A32-244, dated November 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 McDonnell Douglas Corporation, P. O. Box 1771, Long Beach, California 90846-0001, Attention: Business Unit Manager, Technical Publications, C1-HDR (54-60). Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\tAirworthiness Directive 91-22-07 supersedes AD 91-03-07, Amendment 39-6869. \n\n\tThis amendment (39-8067, AD 91-22-07) becomes effective on December 3, 1991.