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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.
90-20-01: 90-20-01 FUJI HEAVY INDUSTRIES LTD: Amendment 39-6724. Docket No. 90-CE-22-AD. Applicability: Model FA-200 (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated in the body of the AD after the effective date of this AD, unless already accomplished. To preclude the loss of control of the airplane, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) and every 100 hours TIS thereafter: (1) Inspect the gust lock pin holes in accordance with FUJI Service Bulletin (S/B) No. 200-008, Revision B, dated May 30, 1989, for burrs and cracks in and around the gust lock pin holes using a 10x magnifying glass. Before further flight: (i) Remove burrs in accordance with the instructions of S/B No. 200-008, Revision B; and (ii) If cracks are found, replace the control column with a serviceable airworthy unit. (2) Inspect the rudder control system in accordance with S/B No. 200-002, Revision C, dated June 5, 1989. Before further flight: (i) Adjust and/or modify rudder stop clearance if required in accordance with the instructions in S/B No. 200-002, Revision C. (ii) Adjust the brake master cylinder rod length in accordance with the instructions in S/B No. 200-002, Revision C. (iii) If the brake link over centers when a force of less than 44 lbs. (20 kg) is applied, replace the defective parts in accordance with the instructions in S/B No. 200-002, Revision C, and retest. (b) Upon incorporating an improved control column in accordance with FUJI Technical Bulletin (T/B) No. 200-020, dated May 30, 1989, the repetitive inspections of the control column specified in paragraph (a)(1) of this AD may be discontinued. (c) Upon incorporation of T/B No. 200-022, dated June 5, 1989; (1) The inspection interval for verifying the cylinder rod length specified in paragraph (a)(2)(ii) of this AD may be increased to 1,000 hours TIS; and, (2)The repetitive brake link over-centering test specified in paragraph (a)(2)(iii) of this AD may be discontinued. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where 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 approved by the Manager, Los Angeles Aircraft Certification Office, 3229 E. Spring St., Long Beach, California 90806-2425; Telephone (213) 988-5200. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to FUJI Heavy Industries, Ltd., Subaru Building, Shinjuku, Tokyo, Japan; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6724, AD 90-20-01) becomes effective on October 22, 1990.
87-25-51: 87-25-51 AEROSPATIALE: Amendment 39-5828. Applies to all Model ATR-42 airplanes, certificated in any category. Compliance is required within the next 10 hours time-in-service, unless previously accomplished. To prevent loss of aileron control due to autopilot servo freezing, accomplish the following: A. Modify the autopilot roll actuator, part number 7002260-922, in accordance with paragraphs 2a, 2b, 2c, 2d, 2f, and 2g of Honeywell, Inc., Sperry Commercial Flight Systems Group, Service Bulletin 21-1987-063, dated October 20, 1987. In performing this modification, ensure that foreign debris does not enter the internal portions of the actuator. B. Inspect all ATR-42 autopilot roll actuators, part number 7002260-922, to ensure that the rubber plug (part number 7013335) has not been installed in the drain hole. C. An alternate means of compliance or adjustment of compliance time, which provides an acceptable level of safety and which has the concurrence of an FAAPrincipal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer, may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulose Cedex 03, France, These documents 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 was effective earlier to all recipients of telegraphic AD T87-25-51, dated December 4, 1987. This amendment 39-5828 becomes effective February 4, 1988.
2012-13-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by several reports of electrical arcs at terminal ''A'' of the electrically heated flight deck window 1. This AD requires repetitive inspections for damage of the electrical connections at terminal ''A'' of the left and right flight deck window 1, and corrective actions if necessary. This AD also allows for replacing a flight deck window 1 with a new improved flight deck window 1 equipped with different electrical connections, which would terminate the repetitive inspections for that window. We are issuing this AD to prevent smoke and fire in the cockpit, which could lead to loss of visibility, and injuries to or incapacitation of the flight crew.
98-05-17: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA-365N, SA-365N1, AS-365N2, and SA-366G1 helicopters. This action requires inspecting for rotational play or looseness of the outboard fin attachment studs (studs) and washers (if washers are present); inspecting each stud for incremental rotational movement or pure rotation; and if there is rotational play or looseness of any individual stud, performing a dye-penetrant inspection for cracks on each stud utilized in the installation. This amendment is prompted by a report of an outboard fin separating from the helicopter during flight, and several reports of loose outboard fins in service. This condition, if not corrected, could result in an outboard fin separating and contacting the rotor blades during flight, and subsequent loss of control of the helicopter.
59-17-04: 59-17-04 COLONIAL: Applies to All Models C-1 and C-2 Aircraft. Compliance required within the next 10 hours but not later than October 15, 1959, and at each 100 hours thereafter. Due to failures in service, remove, inspect, and replace, if damaged, the two AN 4 bolts attaching the wing rear spar to the hull on each side at hull Station 138. The bolts are located adjacent to the inboard flap hinge and are accessible through the wheel wells. Remove only one bolt per side at a time and replace before removing the other bolt. The torque applied to these bolts shall not exceed 70 inch-pounds.
86-25-01: 86-25-01 COLLINS AVIONICS DIVISION/ROCKWELL INTERNATIONAL: Amendment 39-5502. Applies to Model 51RV-4 VOR-ILS Navigation Receivers, Part Number 622-3255-XXX, Serial Number 5960 thru and including 7277, certificated to the applicable requirements of Technical Standard Orders C34c, C36c and C40a. Compliance: Required as indicated in the body of this AD unless already accomplished. To prevent deviation output signal oscillation that may cause undetected erroneous VOR and ILS localizer deviation display, flight director commands, and/or autopilot tracking, accomplish the following: (a) For Model 51RV-4 navigation receivers not installed in an aircraft, prior to further use, modify the unit in accordance with the instructions contained in Collins Alert Service Bulletin A22 dated November 25, 1986. (b) For Model 51RV-4 navigation receivers installed in an aircraft, accomplish the following: (1) For installations approved for Category II, III, and/or autoland operations; within three calendar days after the effective date of this AD, fabricate and install on the instrument panel adjacent to the receiver control head and visible to the pilots the following placard using letters of a minimum 0.10 inch in height: "CATEGORY II/III/AUTOLAND: (as appropriate) "OPERATIONS PROHIBITED." and operate the aircraft accordingly. The placard required by this paragraph may be installed by the holder of a pilot certificate issued by the FAA and valid for the aircraft in which the equipment is installed. (2) Within three calendar days after the effective date of this AD, fabricate and install on the instrument panel adjacent to the receiver control head and visible to the pilots the following placard using letters of a minimum 0.10 inch in height: "AP/FD NOT TO BE COUPLED TO VOR/LOC." and operate the aircraft accordingly. The placard required by this paragraph may be installed by the holder of a pilot certificate issued by the FAA and valid for the aircraft in which the equipment is installed. (3) Within three calendar days after the effective date of this AD, unless already verified within the preceding two calendar days prior to the effective date of this AD; verify localizer centering using a calibrated reference signal or operational ILS localizer signal. This test may be accomplished by alignment of the aircraft on the centerline of a runway served by an ILS signal and observing the HSI (CDI) centering is within two needlewidths of center. Verify VOR centering by using a calibrated reference signal or approved VOR test location (VOT) and observing the HSI (CDI) centering is within plus/minus 2 1/2 degrees. These tests must be accomplished with the receiver installed in the aircraft in its normal configuration. If either test produces unsatisfactory results, the navigation receiver must be removed from service. These tests may be accomplished by the holder of a pilot certificate issued by the FAA and valid for the aircraft in which the equipment is installed. (4) Within 30 calendar days after the effective date of this AD, modify the effected receiver in accordance with the instructions contained in Collins Alert Service Bulletin A22 dated November 25, 1986, or replace with a serviceable unit. (5) Upon modification of the navigation receiver in accordance with the instructions contained in Collins Alert Service Bulletin A22 dated November 25, 1986, the requirements of paragraphs (b)(1), (b)(2), and (b)(3) of this AD no longer apply. (c) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 under visual meteorological conditions to a location where this AD can be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Collins Avionics Division, 400 Collins Road NE, Cedar Rapids, Iowa 52498; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 6, 1987, to all persons except those to whom it has already been made effective by priority letter from the FAA dated December 5, 1986, and is identified as AD 86-25-01.
84-12-04: 84-12-04 MITSUBISHI: Amendment 39-4883. Applies to Models MU-2B, -10, -15, 20, 25, -26, -26A, -30, -35, 36, 36A, 40, and -60 Serial Numbers 1 up to and including 1564 with or without the SA suffix airplanes certificated in any category. NOTE: The serial numbers of airplanes manufactured in the United States by Mitsubishi Aircraft International, Inc. (MAI) are suffixed by "SA." The serial numbers of airplanes manufactured in Japan by Mitsubishi Heavy Industries, Ltd. (MHI) have no suffix. Compliance: Required as indicated, unless already accomplished. To prevent malfunction of the engine air inlet anti-ice system, accomplish the following: (a) Within the next 25 hours time-in-service after the effective date of this AD, install on the main instrument panel, in full view of the pilot, a temporary placard, having letters at least 0.10 inch high, which reads as follows: "FLIGHT INTO KNOWN ICING IS PROHIBITED." (b) Within the next 100 hours time-in-service after the effective date of this AD, retorque and lockwire safety the bleed air tubing coupling nuts: (1) On the MHI airplanes, in accordance with the instructions contained in Mitsubishi MU-2 Service Bulletin No. 196A, dated April 12, 1984, and (2) On the MAI airplanes in accordance with the instructions contained in Mitsubishi Aircraft International, Inc., MU-2 Service Bulletin No. 047/30-001 dated February 20, 1984. (c) When paragraph (b) of this AD has been accomplished, the placard specified in paragraph (a) is no longer required and shall be removed from the airplane. (d) Airplanes may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (e) An equivalent method of compliance with this AD may be used on the MHI airplanes, if approved by the Manager, Western Aircraft Certification Office, ANM-170W, Federal Aviation Administration, P.O. Box 92007, Worldway Postal Center, Los Angeles, California90009, and on the MAI airplanes, if approved by the Manager, Airplane Certification Branch, ASW-150, Federal Aviation Administration, Southwest Region, P.O. Box 1689, Fort Worth, Texas 76101. This amendment becomes effective on June 28, 1984.
2012-13-08: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-200B, 747- 200C, 747-200F, 747-400F, 747SR, and 747SP series airplanes, without a stretched upper deck or stretched upper deck modification. That AD currently requires repetitive inspections for cracks of each affected tension tie and of the surrounding structure, and related investigative and corrective actions if necessary. This new AD requires, for certain airplanes, modifying the tension tie structure or tension tie and frame structure at certain stations; and a post-modification inspection of the modified area and post-modification repetitive inspections of the unmodified area, and repair if necessary. Doing the modification would terminate the repetitive inspection requirements in the existing AD. This AD reduces the compliance time and adds inspections for certain airplanes. This AD was prompted by reports that certain airplanes have tension ties thatare susceptible to widespread fatigue damage. This AD also results from reports of cracks on the forward and aft tension tie channels at station (STA) 740 and STA 760, and a determination that initial inspection intervals need to be reduced. We are issuing this AD to prevent tension ties from becoming severed or disconnected from the frames, which could lead to rapid in-flight decompression.
98-05-14: This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company Models T210N, P210N, and P210R airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
92-27-03: 92-27-03 DE HAVILLAND, INC.: Amendment 39-8436. Docket No. 92-NM-158-AD. Applicability: Model DHC-7 series airplanes; serial numbers 1 through 7, inclusive, and 9, 10, and 11; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the engine nacelles, accomplish the following: (a) Within 6 months after the effective date of this AD, conduct an inspection to determine whether rivets that secure the upper longerons in each inner engine nacelle have been installed, in accordance with de Havilland Service Bulletin 7-54-9, dated February 29, 1980. (1) If any rivets are missing, prior to further flight, accomplish Modification No. 7/1707, in accordance with the service bulletin. (2) If all rivets are detected, no further action is required by this AD. (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, New York Aircraft Certification Office (ACO), ANE-170, FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York 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 inspection and modification shall be done in accordance with de Havilland Service Bulletin 7-54-9, dated February 29, 1980. 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; 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.
98-05-15: This amendment adopts a new airworthiness directive (AD) that applies to SIAI Marchetti, S.r.1 Models SF600 and SF600A airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
98-05-10: This amendment adopts a new airworthiness directive (AD) that is applicable to Robinson Helicopter Company (Robinson) Model R44 helicopters. This action requires replacing the aluminum elbows that connect the oil cooler lines to the engine accessory case with steel elbows. This amendment is prompted by two reports of cracks that were discovered in aluminum elbows. The actions specified in this AD are intended to prevent failure of either the 45 degree or 90 degree aluminum elbows that connect the oil lines from the oil cooler to the engine accessory case, which would cause loss of engine oil, resulting in an engine failure and a subsequent forced landing.
85-21-07 R1: 85-21-07 R1 BEECH: Amendment 39-5295 as amended by 39-5637. Applies to Models 1900 (Serial Numbers UA-1 through UA-3) and 1900C (Serial Numbers UB-1 through UB-60) airplanes certificated in any category. Compliance: Required within 10 hours time-in-service after receipt of this AD, unless already accomplished. To ensure that required performance can be achieved for each approved combination of takeoff configuration, weight, altitude, and temperature, accomplish the following: (a) Revise Beech Model 1900/1900C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM), P/N 114-590021-3, in accordance with Model 1900 and 1900C interim Addendum to POH/AFM, P/N 114-590021-3, dated October 21, 1985. NOTE: The above cited interim Addendum was transmitted to Model 1900/1900C operators of record by Beech letter 52-85-1948, dated October 21, 1985. (b) Conduct further operations in accordance with the POH/AFM so revised. (c) The requirementsof paragraph (a) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. (d) The requirements of paragraphs (a), (b), and (c) do not apply to airplanes which have installed Beech Kit Part Number (P/N) 114-4013-1 S. Airplanes with this kit installed may operate in accordance with the limitations and procedures shown in Beech Model 1900/1900C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM), P/N 114- 590021-3. (e) An equivalent means of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to hereinupon request to Mr. Lou Gollin, Beech Aircraft Service Engineering, Department 52, P.O. Box 85, Wichita, Kansas 67201; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-5295 became effective May 6, 1986. This amendment, 39-5637, becomes effective on July 10, 1987.
92-19-04: 92-19-04 AIRBUS INDUSTRIE: Amendment 39-8362. Docket No. 91-NM-252-AD. Applicability: Model A300-B4-620, A310-221, A310-222, and A310-322 series airplanes, equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, or JT9D-7R4H1 series engines; and Model A300-B4-622, A300-B4-622R, and A310-324 series airplanes, equipped with Pratt and Whitney PW 4152 or PW 4158 series engines, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the airplane, accomplish the following: (a) Accomplish the requirements of paragraphs (a)(1), (a)(2), and (a)(3) of this AD as follows: For airplanes equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, and JT9D-7R4H1 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW7R4 71-90, Revision 2, dated May 14, 1992, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter JT9/71-00/SS:JDS:0-12-3-1. For airplanes equipped with Pratt and Whitney PW 4152 and PW 4158 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW4NAC 71-86, Revision 2, dated February 28, 1992, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter 4000/71.00/SS:TJF:0-12-03-1. (1) Prior to the accumulation of 500 hours time-in-service after the effective date of this AD, perform a visual inspection to detect cracks or a broken link in the forward engine mount thrust link, in accordance with Part 1 of the applicable service bulletin. (i) If no crack or broken link is found, repeat the visual inspection thereafter at intervals not to exceed 1,000 landings until the requirements of paragraph (a)(2) of this AD are accomplished. (ii) If any crack or a broken link is found as a result of the visual inspection, prior to further flight, replace the link with a serviceable part that has been inspected in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (a) of this AD. (2) At the next engine removal or within 4,000 hours time-in-service after the effective date of this AD, whichever occurs first, perform a initial etch inspection to detect cracks or a broken link in the forward engine mount thrust link, in accordance with the applicable service bulletin. (i) If no crack is found as a result of the initial etch inspection, reinstall the link assembly in accordance with the applicable service bulletin. No further action is required. (ii) If any crack or broken link is found as a result of the initial etch inspection, prior to further flight, replace the link with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (a) of this AD. (3) Replacement of the forward engine mount thrust link in accordance with the applicable service bulletin constitutes terminating action for the requirements of this AD. (b) Accomplish the requirements in paragraphs (b)(1), (b)(2), (b)(3), and (b)(4) of this AD as follows: For airplanes equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, and JT9D-7R4H1 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW7R4 71-100, Revision 1, dated July 25, 1991, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter JT9/71-00/SS:0-12-3-1. For airplanes equipped with Pratt and Whitney PW 4152 and PW 4158 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW4NAC 71-105, Revision 1, dated July 25, 1991, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter 4000/71-00/SS:TJF:0-12-03-1. (1) Prior to the accumulation of 500 hours time-in-service after the effective date of this AD, perform a visual inspection to detect cracks or forging laps in the aft engine mount beam assembly, in accordance with Part 1 of the applicable service bulletin. (i) If no crack or forging lap is found as a result of the visual inspection, repeat the visual inspection thereafter at intervals not to exceed 1,000 landings until the requirements of paragraph (b)(2) of this AD are accomplished. (ii) If any crack is found as a result of the visual inspection, prior to further flight, perform a dip etch and a spot fluorescent penetrant inspection to confirm the findings of cracks or forging laps, in accordance with Part 2 of the applicable service bulletin. If any finding of cracks or forging laps is confirmed, prior to further flight, replace the defective beam assembly with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (b) of this AD. As of the effective date of this AD, none of the aft beam assemblies listed in the applicable service bulletin shall be installed on any airplane. (2) Except as provided by paragraph (b)(3) of this AD, at the next engine removal or within 4,000 hours time-in-service after the effective date of this AD, whichever occurs first, perform a dip etch and a fluorescent penetrant inspection to detect cracks or forging laps in the aft engine mount beam assembly, in accordance with Part 2 of the applicable service bulletin. (i) If no crack or forging lap is found as a result of the dip etch and fluorescent penetrant inspection, reinstall the beam assembly in accordance with the applicable service bulletin. No further action is required. (ii) If any crack or forging lap is found as a result of the dip etch and fluorescent penetrant inspection, prior to further flight, replace the beam assembly with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (b) ofthis AD. (3) If the requirements of paragraph (b)(2) of this AD result in a dual engine removal, the dip etch and fluorescent penetrant inspection of one of the two aft engine mounts may be deferred to the next 4,000 hours time-in-service or engine removal, whichever occurs first, provided no crack or forging lap is found while accomplishing the visual inspections required by paragraph (b)(1) of this AD. If those inspections are deferred, repeat the visual inspection of the deferred aft engine mount, as required by paragraph (b)(1) of this AD, at intervals not to exceed 1,000 landings. (4) Replacement of the aft engine mount beam assembly, in accordance with the applicable service bulletin, constitutes terminating action for the requirements of paragraph (b) 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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The inspection and replacement shall be done in accordance with the following Pratt and Whitney service bulletins, as applicable, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page PW4NAC 71-105, Revision 1, July 25, 1991, 1-19 1 July 25, 1991, 1-2 3, 6, 8, 11-16, 18 2 1 February 28, 1992 July 25, 1991PW4NAC 71-86, Revision 2, February 28, 1992 4-5, 7, 9-10, 17 Original May 10, 1991 1, 16-20 2, 4-5, 7, 10 2 Original May 14, 1992 May 10, 1991 PW7R4 71-90, Revision 2, May 14, 1992 3, 6, 8-9, 11-15 1 July 25, 1991 PW7R4 71-100, Revision 1, July 25, 1991 1, 4, 6-18 2-3, 5 1 Original July 25, 1991 May 10, 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, 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 November 17, 1992.
2012-12-03: We are superseding an existing airworthiness directive (AD) for all Rolls-Royce plc (RR) models RB211-Trent 970-84, 970B-84, 972- 84, 972B-84, 977-84, 977B-84, and 980-84 turbofan engines. That AD currently requires inspecting the intermediate-pressure (IP) shaft rigid coupling splines for wear resulting in rearward movement of the IP turbine. This AD requires the same inspections, and new inspections based on possible changes in wear rate. This AD was prompted by RR identifying wear beyond engine manual limits on the abutment faces of the splines. RR also determined that an additional IP shaft rigid coupling configuration requires inspection. We are issuing this AD to detect wear on the abutment faces of the splines, which could result in loss of disc integrity, an uncontained failure of the engine, and damage to the airplane.