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2004-07-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -100B, -100B SUD, -200B, - 200C, -200F, -300, 747SR, and 747SP series airplanes equipped with Pratt & Whitney JT9D-3, -7, -7Q, and -7R4G2 series engines. This amendment requires drilling witness holes through the cowl skin at the cowl latch locations in the left-hand side of the cowl panel assembly of each engine. This action is necessary to prevent improper connection of the latch, which could result in separation of a cowl panel from the airplane. Such separation could cause damage to the airplane, consequent rapid depressurization, and hazards to persons or property on the ground. This action is intended to address the identified unsafe condition.
90-02-22: 90-02-22 DEHAVILLAND: Amendment 39-6471. Applicability: Models DHC-2 Mk. I (including L-20A, YL-20, U-6, and U-6A), and DHC-2 Mk. II (serial numbers 1 through 1056) airplanes certificated in any category. Compliance: Required as indicated in the body of the AD. To ensure the structural integrity of the horizontal tailplane to fuselage front attachment brackets, accomplish the following: (a) Within the next 200 hours time-in-service (TIS), or prior to the accumulation of 1000 hours TIS, whichever occurs later after the effective date of this AD, unless already accomplished per the requirements of AD 54-11-01, and thereafter at intervals not to exceed 1000 hours TIS: (1) Inspect attachment brackets, part number (P/N) C2-FS-543A and P/N C2-FS-544A for cracks and distorted rivets in accordance with paragraph `A' of the "ACCOMPLISHMENT INSTRUCTIONS" in deHavilland Service Bulletin (S/B) No. 2/42, Revision C, dated February 2, 1989. (2) Prior to furtherflight replace any distorted rivets as indicated in the above S/B, paragraph "B", and any cracked brackets as indicated in paragraph "C" of the Service Bulletin. (b) At each interval not exceeding 1000 hours TIS since the last bolt replacement, replace all 1/4 inch diameter forward attachment bolts on the tailplane front attachment brackets with new bolts, P/N AN174-H12A, in accordance with S/B No. 2/42 Rev C. (c) The repetitive inspections or modifications in paragraph (a) of this AD are not required on airplanes modified in accordance with deHavilland Modification No. 2/1338, or Agriculture Modification No. 2/984, as applicable. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where the requirements of this AD may be accomplished. (e) An alternate method of compliance or adjustment of the initial or repetitive compliance times, which provides an equivalent level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region, 181 South Franklin Avenue, Valley Stream, New York 11581. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Boeing of Canada, Ltd.; deHavilland Division, Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5; Telephone (416) 633-7310; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD supersedes AD 54-11-01. This amendment (39-6471, AD 90-02-22) becomes effective on February 13, 1990.
2021-13-11: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2D15 (Regional Jet Series 705) and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a report that the lower aft outboard supporting structure of galley 2 does not meet certification requirements for all flight and/or emergency landing loads. This AD requires modifying the floor structure between certain fuselage stations. The FAA is issuing this AD to address the unsafe condition on these products.
76-17-04: 76-17-04 ARMSTRONG WHITWORTH: Amendment 39-2701. Applies to all Model AW-650 Series 101 airplanes certificated in all categories. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To detect cracks in the undercut at the bottom of the main undercarriage sliding cylinder and prevent possible failure of the main landing gear, accomplish the following: (a) Inspect the undercut at the bottom of the main undercarriage sliding cylinder with magnetic particle fluid in accordance with Accomplishment Instructions 2A(1) through 2A(6) of Dowty Rotol Service Bulletin No. 32-49D, dated August 15, 1975, or an FAA-approved equivalent. (b) If a crack in the sliding cylinder is detected during the inspection required by paragraph (a) of this AD, replace the main undercarriage sliding cylinder before further flight with a serviceable part of the same part number or an FAA-approved equivalent. This amendment becomes effective on September 9, 1976.
91-05-04: 91-05-04 BOEING: Amendment 39-6907. Docket No. 90-NM-153-AD. \n\n\tApplicability: Model 747-400 series airplanes, listed in Boeing Service Bulletin 747-26- 2138, Revision 1, dated March 1, 1990, and Boeing Service Bulletin 747-26-2141, Revision 1, dated July 12, 1990, certificated in any category. \n\n\tCompliance: Required within the next 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo preclude cross connection of fire extinguishing wiring during maintenance, accomplish the following: \n\n\tA.\tFor airplanes identified in Boeing Service Bulletin 747-26-2138, Revision 1, dated March 1, 1990: Modify the engine fire extinguishing system in accordance with that service bulletin. \n\n\tB.\tFor airplanes identified in Boeing Service Bulletin 747-26-2141, Revision 1, dated July 12, 1990: Modify the fire control module in accordance with that service bulletin. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. \n\n\tThis amendment (39-6907, AD 91-05-04) becomes effective on March 25, 1991.
98-06-05: This amendment adopts a new airworthiness directive (AD) that applies to Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes that are equipped with a Rockwell Collins APS-65 autopilot system that incorporates an APC-65A autopilot computer. This AD requires incorporating airplane flight manual (AFM) and pilot s operating handbook (POH) supplements that include revised autopilot emergency disengagement procedures. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent pilot difficulty in disengaging the autopilot during flight, which could result in the pilot s lack of proper attention to critical flight tasks due to the increased pilot workload with possible consequent loss of airplane controllability.
2021-15-52: The FAA is adopting a new airworthiness directive (AD) for various restricted category helicopters originally manufactured by Bell Textron Inc. This AD was prompted by a fatal accident in which an outboard main rotor hub strap pin (pin) sheared off during flight, resulting in the main rotor blade and the main rotor head detaching from the helicopter. This AD requires removing certain pins from service and prohibits installing those pins on any helicopter. The FAA previously sent an emergency AD to all known U.S. owners and operators of these restricted category helicopters and is now issuing this AD to address the unsafe condition on these products.
2011-15-09: We are adopting a new airworthiness directive (AD) for the products listed above that would [[Page 42034]] supersede an existing AD. 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: Two cases of the main landing gear (MLG) alternate extension system (AES) cam mechanism failure were found during line checks. The cam mechanism operates the cable to open the MLG door and releases the MLG uplock in sequence. In the case where it is necessary to deploy the MLG using the AES, the failure of the MLG AES cam mechanism on one side will lead to an unsafe asymmetrical landing configuration. * * * * * The unsafe condition is possible loss of control during landing. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
92-10-12: 92-10-12 BEECH AIRCRAFT CORPORATION: Amendment 39-8246. Docket No. 91-CE-96-AD. Supersedes AD 91-18-11; Amendment 39-8014. Applicability: The following model and serial number airplanes, certificated in any category: Model Serial Numbers 200 and B200 BB-2 and BB-6 through BB-1404 200C and B200C BL-1 through BL-72 and BL-124 through BL-137 200CT and B200CT BN-1 through BN-4 200T and B200T BT-1 through BT-33 A100-1 (U-21J) BB-3, BB-4, and BB-5 A200 (C-12A) BC-1 through BC-75 A200 (C-12C) BD-1 through BD-30 A200C (UC-12B) BJ-1 through BJ-66 A200CT (C-12D) BP-1, BP-22, and BP-24 through BP-51 A200CT (FWC-12D) BP-7 through BP-11 A200CT (RC-12D) GR-1 through GR-13 A200CT (C-12F) BP-52 through BP-71 A200CT (RC-12G) FC-1, FC-2, and FC-3 A200CT (RC-12H) GR-14 through GR-19 B200C (C-12F) BL-73 through BL-112 and BL-118 through BL-123 B200C (UC-12F) BU-1 through BU-10 B200C (RC-12F) BU-11 and BU-12 B200C (UC-12M) FC-1, FC-2, and FC-3 B200C (RC-12M) BV-11 and BV-12 Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished (superseded AD 91-18-11). To prevent separation of the aft cowling doors, which could result in occupant injury if decompression or structural damage occurs, accomplish the following: (a) Inspect and modify the aft engine cowling doors of both engine nacelles in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beech Mandatory Service Bulletin (SB) No. 2416, Revision I, dated December 1991. (b) If the aft engine cowling doors of both nacelles have been inspected and modified in accordance with the original issue of Beech SB No. 2416, dated July 1991, (as required by superseded AD 91-18-11), then no further action is required by this AD. NOTE 1: The configuration of certain early model airplanes made compliance with the original issue of Beech SB No. 2416 impossible as required by superseded AD 91-18-11. Service (SVR) 025 was approved as an alternative method of compliance for portions of superseded AD 91-18-11 on some of the affected early model airplanes. (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) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (e) The inspections and modifications required by this AD shall be done in accordance with Beech Mandatory Service Bulletin No. 2416, Revision I, dated December 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 the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. 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, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment (39-8246) supersedes AD 91-18-11, Amendment 39-8014. (g) This amendment (39-8246) becomes effective on June 12, 1992.
2004-07-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires replacement of certain assistor springs and bearings with certain new assistor springs and bearings. This action is necessary to prevent possible collapse of a main landing gear upon landing and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.