Results
73-12-09: 73-12-09 ROCKWELL INTERNATIONAL: Amendment 39-1664 is further amended by Amendment 39-2271. Applies to all Model NA-265-40 airplanes, Serial Numbers prior to 282-138 and equipped with thrust reversers; all Model NA-265-60 airplanes, Serial Numbers prior to 306-81, all Model NA-265-70 airplanes, Serial Numbers 370-2 through 370-6, and 370-8 and 370-9. Compliance required as indicated. To prevent unwanted thrust reverser deployment, accomplish (a), or (b), or (c), or (d), below, prior to further flight, except as provided below. (a) (1) Stow and lock the thrust reversers in the forward thrust position and install a placard in plain view of the pilot indicating that the thrust reversers are deactivated. The thrust reversers must be locked in the stowed position in accordance with North American Rockwell Report NA-62-1223, page 68E, for Model NA-265-40; Report NA-66-1030, Operational Supplement No. 8, for Model NA-265-60; and Report NA-69-639, Section 1-47, for Model NA-265-70. (2) Pull and collar, for all affected models, the following electrical circuit breakers located on the copilot side console: "CONTROL LH"; "CONTROL RH"; "LATCH LH"; "LATCH RH"; "EMERG STOW"; and "IND LTS". (b) (1) Incorporate the revisions, dated May 16, 1973, to the FAA-approved NA-265 series Sabreliner Airplane Flight Manuals, CERTIFICATE LIMITATIONS, EMERGENCY PROCEDURES and NORMAL PROCEDURES sections, pertaining to thrust reverser operation. References: NA-62-1300; NA-72-25; NA-66-1030; and NA-69-422. (2) Prior to the first flight of each day, perform the pre-flight operational check in accordance with North American Rockwell Service Bulletin 73-10, Addendum A, dated May 16, 1973, or later FAA-approved revisions of the Sabreliner 40/60 series Maintenance Manual TR-78-9; or -70 series Maintenance Manual TR-78-3. Install a placard in plain view of the pilot to require performance of this pre-flight thrust reverser system check. (3) Perform the rigging inspections of the thrust reverser in accordance with Service Bulletin 73-10 dated May 16, 1973, or later FAA-approved revisions. (4) Perform a one-time "Thrust Reverser 100-hour Inspection" per Addendum B, Service Bulletin 73-10, dated May 16, 1973 or later FAA-approved revisions. (5) Within three hundred hours additional time in service, perform a one- time "Operational Check of Thrust Reverser Relays" per Addendum C, Service Bulletin 73-10, dated May 16, 1973, or later FAA-approved revisions. (6) Thereafter, the inspections specified in paragraphs (b) (3), (4), and (5) above, may be performed as normal maintenance procedures in accordance with the North American Sabreliner Maintenance Manuals applicable to the model. (7) Accomplish the wiring change to the dimming circuit in accordance with North American Service Bulletin 73-6, dated May 16, 1973, or later FAA-approved revisions. (8) Aircraft which cannot meet or otherwise comply with any of the inspectionor installation requirements of paragraph (b) of this AD, can be operated only per paragraphs (a) or (c) of this AD. (c) (1) Install a strengthened stang bracket in accordance with FAA Approved Sabreliner Division Service Bulletin 74-11, dated June 20, 1975, or later FAA-approved revisions; and (2) Install an automatic Stow System in accordance with Sabreliner Division FAA Approved Service Bulletin 74-8 dated July 14, 1975, or later FAA-approved revisions; and (3) Incorporate in the Airplane Flight Manual the appropriate revisions shown in Sabreliner Division Service Bulletin (2), above. NOTE: For the purpose of compliance with (c), above, the automatic stow system must be operational. (d) Equivalent inspections, maintenance procedures, and installations may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. AD 73-12-09 , Amendment 39-1664 supersedes A AD 73-10-04. Amendment 39-1664 was effective June 16, 1973 for all persons except those to whom it was made effective immediately by airmail letter dated May 17, 1973, which contained this amendment. This amendment becomes effective July 29, 1975.
91-15-08: 91-15-08 BRITISH AEROSPACE (BAE), LIMITED: Amendment 39-7071. Docket No. 91-CE-52-AD. Applicability: Jetstream HP 137 Mk1, Models 200, 3101, and 3201 airplanes (all serial numbers), certificated in any category. Compliance: Required initially as follows, unless already accomplished, and thereafter at intervals not to exceed 10,000 landings: o For airplanes with less than 9,500 landings on the effective date of this AD, prior to the accumulation of 10,000 landings. o For airplanes with 9,500 landings or more but less than 10,000 landings on the effective date of this AD, prior to the accumulation of 10,500 landings. o For airplanes with 10,000 or more landings but less than 12,000 landings on the effective date of this AD, within the next 500 landings. o For airplanes with 12,000 or more landings but less than 15,000 landings on the effective date of this AD, within the next 150 landings. o For airplanes with over 15,000 landings on the effective date of this AD, within the next 50 landings. NOTE: If no record of landings is maintained, hours time-in-service (TIS) may be used with one hour TIS equal to two landings. For example, 100 hours TIS is equal to 200 landings. To prevent the loss of control of engine power, accomplish the following: (a) Replace the engine power lever control cables (all 8) with new power lever control cables in accordance with the instructions in BAe SB 76-A-JA 910542, dated May 30, 1991. (b) 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. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. 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) The replacements required by this AD shall be done in accordance with BAe SB 76-A-JA 910542, dated May 30, 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 British Aerospace, Manager Product Support, Commercial Aircraft Limited, Airlines Division, Prestwick Airport, Ayrshire, KA9 2RW Scotland; or British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, DC 20041. 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. This amendment (39-7071, AD 91-15-08) becomes effective on August 12, 1991.
90-07-07: 90-07-07 BRITISH AEROSPACE, PLC: Amendment 39-6553. Docket No. 89-NM-257-AD. Applicability: Model BAe-146 series airplanes, on which Modification HCM50075A, B, and C have been incorporated, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To prevent brake drag or complete loss of braking, accomplish the following: A. Inspect the quick-disconnect couplings in the yellow and auxiliary systems hydraulic lines to the wheel brake units on the left and right main landing gear for tightness, retighten to finger-tight torque, and secure the quick-disconnect couplings with a corrosion-resistant steel lockwire, in accordance with British Aerospace Service Bulletin 32-A101, dated September 1, 1989. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P. O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6553, AD 90-07-07) becomes effective onApril 30, 1990.
2012-12-08: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of cracked retract actuator fuse pins that can fail earlier than the previously determined safe life limit of the pins. A fractured retract actuator fuse pin can cause the main landing gear to extend without restriction and attempt to lock into position under high dynamic loads. This AD requires an inspection for the part number of the fuse pin, and replacement of the pin if necessary. We are issuing this AD to prevent structural damage to the side and drag brace lock assemblies, which could result in landing gear collapse during touchdown, rollout, or taxi.
98-06-03: This amendment adopts a new airworthiness directive (AD) that applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Model EA-300 airplanes. This AD requires removing the elevator mass balance assemblies and replacing them with reinforced elevator mass balance assemblies of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent damage and possible jamming of the airplane s control system, which, if not corrected, could cause loss of control of the airplane.
92-17-01: 92-17-01 BEECH: Amendment 39-8330. Docket No. 92-CE-24-AD. Supersedes AD 80-21-02, Amendment 39-3968. Applicability: The following Model airplanes, certificated in any category: 1. A36TC, serial numbers EA-1 through EA-146. 2. S35, V35, V35A and V35B, serial numbers D-7 140 and D-7310 through D-10403, that are equipped with an optional Teledyne Continental Motors (TCM) TSIO-520-D engine. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent a fire in the engine compartment of the airplane caused by fuel leaks from the fuel metering unit or the idle mixture adjustment screw boss, accomplish the following: (a) For Model A36TC airplanes, determine whether a fuel drain hose is installed by accomplishing paragraphs 1. and 2. of PART I of the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin (SB) No. 2420, dated February 1992. (1) If a fuel drain hose isnot installed, prior to further flight, accomplish the following: (i) Inspect the fuel metering unit for fuel leaks in accordance with paragraph 2. of PART II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2420, dated February 1992. (ii) Repair any fuel metering units found leaking as a result of the inspection required by paragraph (a)(1)(i) of this AD in accordance with paragraphs 3. and 4. of PART II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2420, dated February 1992. (iii) Install a fuel drain hose, part number (P/N) 106200G8-288, over the idle mixture screw boss in accordance with paragraphs 5. through 8. of PART II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2420, dated February 1992. (2) If a fuel drain hose is installed, prior to further flight, accomplish the following: (i) Inspect the fuel metering unit for fuel leaks in accordance with paragraph 2. of PART II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2420, dated February 1992. (ii) Repair any fuel metering units found leaking as a result of the inspection required in paragraph (a)(2)(i) of this AD in accordance with paragraphs 3. and 4. of PART II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2420, dated February 1992. (iii) Check the condition of the fuel drain hose, and replace any hose that is deteriorated with a new hose, P/N 106200G8-288, in accordance with paragraphs 5. through 8. of PART II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2420, dated February 1992. (b) For Models S35, V35, V35A and V35B airplanes that are equipped with an optional TCM TSIO-520-D engine, accomplish the following: (1) Inspect the fuel metering unit for fuel leaks in accordance with paragraph 2. of PART II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2420, dated February 1992. (2) Prior to further flight, repair any fuel metering units found leaking as a result of the inspection required by paragraph (b)(1) of this AD in accordance with paragraphs 3. and 4. of PART II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2420, dated February 1992. (3) Install a fuel drain hose, part number (P/N) 106200G8-288, over the idle mixture screw boss in accordance with paragraphs 5. through 8. of PART II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2420, dated February 1992. (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, Room 100, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita Aircraft Certification Office. NOTE: 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, installation, and possible repairs required by this AD shall be done in accordance with Beech Service Bulletin No. 2420, dated February 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 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, 800 North Capitol Street, N.W.; 7th Floor, Suite 700; Washington, DC. (f) This amendment supersedes AD 80-21-02, Amendment 39-3968. (g) This amendment becomes effective on September 11, 1992.
2012-13-02: We are superseding an existing airworthiness directive (AD) for all Pratt & Whitney Division PW4074 and PW4077 turbofan engines. That AD currently requires removing the 15th stage high-pressure compressor (HPC) disk within 12,000 cycles since new (CSN) or using a drawdown removal plan for disks that exceed 12,000 CSN. This new AD requires the same actions and clarifies that 15th stage HPC disks that have accumulated more than 9,865 CSN require a borescope inspection (BSI) or eddy current inspection (ECI) of the disk outer rim front rail for cracks prior to accumulating 12,000 CSN. This AD was prompted by a request from an operator that we clarify our inspection schedule for 15th stage HPC disks that have accumulated more than 9,865, but less than 12,000 CSN, on the effective date of the AD. We are issuing this AD to prevent cracks from propagating into the disk bolt holes, which could result in a failure of the 15th stage HPC disk, uncontained engine failure, and damage to theairplane.
97-26-17: This document makes a correction to airworthiness directive (AD) 97-26-17 applicable to certain Teledyne Continental Motors (TCM) IO-520 and TSIO-520 engines that was published in the Federal Register on December 19, 1997 (62 FR 66502). The address information for the contact engineer in the For Further Information Contact section and the manufacturer s telephone number in the Addresses section and paragraph (f) of the Compliance Section is incorrect. This document corrects that information. In all other respects, the original document remains the same. DATES: Effective January 23, 1998.
98-05-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model DH 125-1A and -3A series airplanes, that requires repetitive eddy current inspections to detect fatigue cracking of the main entry door/frame pressing, and repair, if necessary. This amendment is prompted by reports of fatigue cracking of the main entry door/frame pressing due to cyclic loading of the door frame. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could lead to the loss of structural integrity of the main entry door, and, consequently, result in decompression of the cabin.
92-16-51: 92-16-51 EMBRAER: Amendment 39-8355. Docket No. 92-NM-152-AD. Applicability: All Model EMB-120 series airplanes, certificated in any category. To prevent an inoperative backup flight idle stop system and potential engine failure, accomplish the following: (a) Within 5 days after the effective date of this AD, and thereafter prior to the first flight of each day, accomplish paragraph (a)(1) or (a)(2) of this AD, as applicable: (1) For airplanes on which an inspection window has been installed on the left lateral console panel that permits visibility of the flight idle stop solenoid circuit breakers: Using an appropriate light source, perform a visual check to verify that both "FLT IDLE STOP SOL" circuit breakers CB0582 and CB0583 for engine 1 and engine 2 are closed. NOTE 1: This check may be performed by a flight crew member. NOTE 2: Instructions for installation of an inspection window can be found in EMBRAER Information Bulletin 120-076-0003, dated November 19, 1991; or EMBRAER Service Bulletin 120-076- 0014, dated July 29, 1992. (2) For airplanes on which an inspection window has not been installed on the left lateral console panel: Perform a visual inspection to verify that both "FLT IDLE STOP SOL" circuit breakers CB0582 and CB0583 for engine 1 and engine 2 are closed. (b) As a result of the check or inspection performed in accordance with paragraph (a) of this AD: If circuit breakers CB0582 and CB0583 are not closed, prior to further flight, reset them and perform the functional test specified in paragraph (c) of this AD. (c) Within 5 days after the effective date of this AD and thereafter at intervals not to exceed 75 hours time-in-service, or immediately following any maintenance action where the power levers are moved with the airplane on jacks, conduct a functional test of the backup flight idle stop system for engine 1 and engine 2 by performing the following steps: (1) Move both power levers to the "MAX" position. (2) Turn the aircraft power select switch on. (3) Open both "AIR/GROUND SYSTEM" circuit breakers CB0283 and CB0286 to simulate in-flight conditions with weight-off-wheels. Wait for at least 15 seconds, then move both power levers back toward the propeller reverse position with the flight idle gate triggers raised. Verify that the power lever for each engine cannot be moved below the flight idle position, even though the flight idle gate trigger on each power lever is raised. (4) If the power lever can be moved below the flight idle position, prior to further flight, restore the backup flight idle stop system to the configuration specified in EMBRAER Service Bulletin 120-076-0009, Change No. 4, dated November 1, 1990, and perform a functional test. NOTE: If the power lever can be moved below flight idle, this indicates that the backup flight idle stop system is inoperative. (5) Move both power levers to the "MAX" position. (6)Close both "AIR/GROUND SYSTEM" circuit breakers CB0283 and CB0286. Wait for at least 15 seconds, then move both power levers back toward the propeller reverse position with the flight idle gate triggers raised. Verify that the power lever for each engine can be moved below the flight idle position. (7) If either or both power levers cannot be moved below the flight idle position, prior to further flight, inspect the backup flight idle stop system and the flight idle gate system, and accomplish either paragraph (c)(7)(i) or (c)(7)(ii) of this AD, as applicable: (i) If the backup flight idle stop system is failing to disengage with weight- on-wheels, prior to further flight, restore the system to the configuration specified in EMBRAER Service Bulletin 120-076-0009, Change No. 4, dated November 1, 1990. (ii) If the flight idle gate system is failing to open even though the trigger is raised, prior to further flight, repair in accordance with the EMBRAER Model EMB-120maintenance manual. (8) Turn the power select switch off. The functional test is completed. (d) Within 10 days after accomplishing the initial visual inspection/check and initial functional test required by paragraphs (a) and (c) of this AD, report the results of those tests, positive or negative, to the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349; fax (404) 991-3606. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (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, Atlanta ACO, 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, Atlanta ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (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 restoration procedure shall be done in accordance with EMBRAER Service Bulletin 120-076-0009, Change No. 4, dated November 1, 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 EMBRAER Aircraft Corporation, 276 SW. 34th Street, Fort Lauderdale, Florida 33315. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on September 23, 1992, to all persons except those persons to whom it was made immediately effective by telegraphic AD T92-16-51, issued July 29, 1992, which contained the requirements of this amendment.