Results
56-21-04: 56-21-04 RUSSELL: Applies to Safety Belts Equipped With Russell Manufacturing Co.'s 2 Inch Rusco Tog-L-Lok Safety Belt Buckle. Compliance required as soon as possible but not later than December 30, 1956. Recurring instances have been reported wherein Russell Model RM-3 and RM-4 belt assemblies have slipped and unlocked under relatively low tension loads. Accordingly, it has been determined that safety belt assemblies RM-3 and RM-4 manufactured between July 1, 1954, and August 1, 1956, as meeting Technical Standard Order C22b standards and equipped with Rusco Tog-L-Lok buckles, are unairworthy and must be reworked or replaced with belt assemblies that conform to TSO-C22b standards. Due to the need for precise jigs to accomplish the rework of these assemblies, reworking in the field is not feasible. However, the Russell Manufacturing Co. has submitted satisfactory substantiating data for reworking the unsatisfactory safety belt assemblies at the factory. In addition to the above difficulty, some of the faulty Tog-L-Lok buckles may have been sold as, or on, military surplus equipment and, therefore, there is some likelihood that other companies or individuals may have renovated or manufactured and sold safety belt assemblies which incorporate these faulty buckles. The characteristics of these buckles are such that if the assembly does not slip or unlock under a maximum tensile load of 100 pounds, the belt assembly is satisfactory. Accordingly, a maximum tensile load of 100 pounds need be applied to these belt assemblies to check their airworthiness. If the assembly does not slip or unlock under this load, the assembly may be considered satisfactory and rework or replacement is not necessary.
85-02-02: 85-02-02 AIRBUS INDUSTRIE: Amendment 39-4986. Applies to Model A300 B2 and B4 series airplanes, certificated in all categories. To detect failure of the ram air turbine, accomplish the following, unless previously accomplished: A. Prior to the later of the following: 1. 3,400 hours total time in service; 2. 24 months since installed, either new or overhauled; or 3. 120 days after the effective date of this AD; perform a functional test of the ram air turbine in accordance with the accomplishment instructions of Dowty Rotol Service Bulletins 29-101 dated January 4, 1979, and 29-72 dated April 12, 1976. Repeat the functional test at intervals not to exceed 600 hours time in service or 6 months, whichever occurs first. B. If, as a result of the functional test of paragraph A., above, it is found that the ram air turbine does not meet the specifications, the affected unit must be replaced with a serviceable unit before further flight. C. Termination ofthe requirements of this AD is accomplished by incorporation of the following two Dowty Rotol modifications: RM 401, described in Service Bulletin 29-104 dated January 24, 1979, and RM 370, described in Service Bulletin 29-76 dated November 18, 1976. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective March 1, 1985.
60-26-05: 60-26-05 LOCKHEED: Amdt. 236 Part 507 Federal Register December 22, 1960. Applies to All 188 Series Aircraft. Compliance required as indicated. (a) Within the next 150 hours' time in service commencing on November 22, 1960, unless already accomplished within the last 300 hours' time in service, inspect the elevator counterweight installation, Lockheed Drawing No. 829912, at airplane center line for evidence of free play as follows: with elevator blocked at extreme down position apply up and down force to balance weight Lockheed P/N 827020-1, and measure total movement of balance weight due to cumulative free play in joints of balance arm linkage. If movement of balance weight due to cumulative free play in system exceeds 1/8-inch inspect each joint in balance arm linkage and reduce the free play by bolt and/or part replacement at one or more of these joints so as to reduce total free play movement of the balance weight to 1/16-inch or less prior to further flight. This inspection must be repeated every 450 hours' time in service. When provisions of paragraph (c)(1) are accomplished, this special inspection may be discontinued. (b) Within the next 300 hours' time in service, unless already accomplished within the last 700 hours' time in service, and following any occurrence of inflight elevator or control column oscillations, inspect the elevator booster control valve viscous damper diaphragm, Lockheed P/N 813612-1 for evidence of rupture. See Lockheed Electra (Model 188) Overhaul Manual Section 27-1-10 Page 1 for information on evidence of rupture. If such evidence is found the airplane shall not be returned to service until the diaphragm is replaced with a new part, or compliance with paragraph (c)(2) has been accomplished. This inspection must be repeated at periods not to exceed 1,000 hours' time in service until the provisions of paragraph (c)(2) have been accomplished. (c) The following must be accomplished within the next 1,000 hours' time in service. (1) Install a spring-loaded cartridge, Lockheed P/N 840404-1, in the elevator counterweight linkage in the manner described by Lockheed Service Bulletin 88/SB-524. (2) Replace the elevator boost control valve viscous damper, Lockheed P/N 813608-3, with an orifice type damper, Lockheed P/N 492508-3, in accordance with Lockheed Service Bulletin No. 88/SB-524. (3) Rework the elevator booster assembly in accordance with Lockheed Service Bulletin No. 88/SB-524 to incorporate an orifice valve assembly, Lockheed P/N 804551-1, and modify the booster piston rod end installation to incorporate two retaining washers, Lockheed P/N 839756-1, in accordance with Lockheed Service Bulletin No. 88/SB-498. (FAA approved Lockheed Service Bulletins 88/SB-498 and 88/SB-524, Lockheed Electra operating information letter No. 13 dated November 1, 1960, Lockheed Alert Bulletin No. 524 dated December 1, 1960, cover portions of this subject.) This supersedes AD 60-24-02. Thisdirective effective December 22, 1960.
64-10-05: 64-10-05 PRATT & WHITNEY: Amdt. 724 Part 507 Federal Register May 5, 1964. Applies to All Models R-2800-21, -27, -31, -43, -51, -51M4, -59, -63, -71, -75, -75M2 and -79 Series Engines. Compliance required within 1,400 hours' time in service after the effective date of this AD. Because of instances of exhaust valve failures, replace the P/N 44764 exhaust valves with P/N's 50724 or 158175 exhaust valves. This directive effective June 5, 1964. Revised September 5, 1964.
2005-23-20: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-135 airplanes, and Model EMB-145, -145ER, - 145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD requires modification of the upper frame of the firewall for the auxiliary power unit (APU). This AD results from the discovery of a hole in the upper frame of the firewall for the APU. We are issuing this AD to ensure that the APU compartment is isolated from the rest of the airplane in the event of an APU fire. If the APU compartment is not isolated, smoke could enter the passenger cabin in the event of an APU fire.
99-23-22: This amendment adopts a new airworthiness directive (AD) that is applicable to various transport category airplanes equipped with certain Mode "C" transponder(s) with single Gillham code altitude input. This action requires repetitive tests to detect discrepancies of the Mode "C" transponder(s), air data computer, and certain wiring connections; and corrective actions, if necessary. This amendment is prompted by reports that, during level flight, the Traffic Alert Collision Avoidance System (TCAS II) issued false advisories that directed the flightcrew to change course and either climb or descend. The actions specified in this AD are intended to prevent such false advisories due to inaccurate airplane altitude reporting, which could result in the flightcrew deviating the airplane from its assigned flight path and a possible mid-air collision.
87-02-01: 87-02-01 SCHWEIZER AIRCRAFT CORP.: Amendment 39-5512. Applies to all Schweizer gliders (including kit built), all serial numbers certificated in any category, and all models listed below: SGU 1-7 SGS 2-8 (TG-2) SGS 2-12 (TG-3) SGU 1-19 SGU 1-20 SGU 1-21 SGU 2-22, 2-22A, 2-22C, 2-22CK, 2-22E, 2-22EK SGS 1-23, 1-23B, 1-23C, 1-23D, 1-23E, 1-23F, 1-23G, 1-23H, 1-23H15 SGS 1-24 SGS 1-26, 1-26A, 1-26B, 1-26C, 1-26D, 1-26E SGS 2-32 SGS 2-33, 2-33A, 2-33AK SGS 1-34, 1-34R SGS 1-35C SGS 1-36 (Sprite) Compliance is required as indicated unless already accomplished. To prevent the possibility of the tow-hook inadvertently slipping out of the release-arm and releasing the tow-line, which could result in a forced landing, accomplish the following: (a) Within the next 5 tow release actuations after the effective date of this AD, perform the following: (1) Inspect the tow-release installation for proper part numbers, excessive wear, and possible rework or replacement of parts in accordance with Part 3A, 3B, and 3C in Schweizer Service Bulletin No. SA-001, dated October 3, 1986. (2) Perform the operational check in accordance with Figure 4 in Schweizer Service Bulletin No. SA-001, dated October 3, 1986. (b) Thereafter, at intervals not to exceed 100 hours time-in-service, accomplish the steps in Part 3B, and 3C, and Figure 4 in Schweizer Service Bulletin No. SA-001, dated October 3, 1986. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, Telephone (516) 791-6680. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. Schweizer Service Bulletin No. SA-001, dated October 3, 1986, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not received this document from the manufacturer may obtain copies upon request to Schweizer Aircraft Corp, P.O. Box 147, Elmira, New York 14902, Telephone (607) 739-3821. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 86-ANE-46, Room 311, between the hours of 8:00 a.m. and 4:30 p.m. Monday through Friday, except Federal holidays. This amendment becomes effective on January 21, 1987.
89-07-12: 89-07-12 SIKORSKY AIRCRAFT: Amendment 39-6171. Applicability: Model S-76 series helicopters, certificated in any category, that are equipped with tail rotor horn, P/N 76101-05006. Compliance: Required as indicated, unless already accomplished. To prevent possible fatigue failure of the tail rotor component, which could result in a reduction of directional control and hazardous tail rotor vibration in the helicopter, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD or before the accumulation of 12,000 hours time in service, whichever occurs later, replace the tail rotor horn, P/N 76101-05006, with a serviceable tail rotor horn that has not exceeded 12,000 hours' time in service. Thereafter, replace the tail rotor horn P/N 76101-05006, with a serviceable tail rotor horn before the accumulation of 12,000 hours' time in service. (b) Operators who have not kept records of hours' time in service on individual tail rotor horn component parts must substitute the hours' time in service of the tail rotor blade bonded assembly, P/N 76101-05020 or P/N 76088-20077. (c) For purposes of complying with this AD, the hours' time in service for the individual tail rotor horn and blade components that were not installed at the time of issuance of the initial rotorcraft airworthiness certificate must be determined from rotorcraft records. (d) Upon request, an alternate means of compliance which provides a level of safety equivalent to the requirements of this AD may be used when approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7118. (e) Upon submission of substantiating data by an owner or operator through an FAA Aviation Safety Inspector, the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7118, may adjust the compliance time specified in this AD. This amendment (39-6171, AD 89-07-12) becomes effective on April 27, 1989.
2018-22-07: We are adopting a new airworthiness directive (AD) for all Engine Alliance (EA) GP7270, GP7272, and GP7277 model turbofan engines. This AD requires inspection of the stage 6 seal ring for correct installation and inspection of the high-pressure compressor (HPC) stages 2-5 spool for cracks. This AD also requires replacement of the HPC stages 2-5 spool if the stage 6 seal ring is incorrectly installed or if the HPC stages 2-5 spool is found cracked. This AD was prompted by a shop finding of axial cracks in the interstage 5-6 seal teeth of the HPC stages 2-5 spool spacer arm, due to an incorrectly installed stage 6 seal ring. We are issuing this AD to address the unsafe condition on these products.
98-20-17: This amendment adopts a new airworthiness directive (AD) that applies to certain SAFT America Inc. P/N 021929-000 (McDonnell Douglas P/N 43BO34LB02) and P/N 021904-000 (McDonnell Douglas P/N 43BO34LB03) nickel cadmium batteries that are installed on aircraft. This AD requires replacing all battery terminal screws, verifying that the battery contains design specification cells, and replacing the cells if the battery contains non-design specification cells. This AD is the result of an incident where the cell screws on one of the affected batteries were exposed to chloride, which caused the heads of some fasteners to shear off and eventually resulted in the battery exploding. The actions specified by this AD are intended to prevent such an occurrence, which could result in loss of emergency power to electrical flight components or other emergency power systems required in the event of loss of the aircraft primary power source.
98-20-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100 and -300 series airplanes, that requires inspections to detect corrosion on areas of the airplane structure where black film thermal insulation is used; repair, if necessary; and replacement of black insulation blankets with certain aluminized (silver) insulation. This amendment is prompted by reports of corrosion forming on areas of the airplane structure where the black film covers the thermal insulation blankets. The actions specified by this AD are intended to prevent degradation of the structural capability of the airplane fuselage and sudden loss of cabin pressure due to corrosion of the airplane fuselage structure.
66-09-02: 66-09-02 DOWTY ROTOL: Amdt. 39-215 Part 39 Federal Register March 23, 1966. Applies to Dowty Rotol Propellers, (c) R.193/4-30-4/50, installed on Fairchild F-27; (c) R.184/4- 30-4/50, installed on Grumman G-159; and (c) R.179/4-20-4/33, installed on Viscount 810. Compliance required within the next 200 hours' time in service after the effective date of this AD unless already accomplished. To prevent further improper operation of the propeller pitch lock under high oil temperature conditions, rework the existing Lock Support Sleeve, Dowty Rotol P/N RA.61236, in accordance with Dowty Rotol Service Bulletin No. 61-185 (Modification No. (c) VP.2032) or later ARB-approved revision. This directive effective April 22, 1966. Revised June 16, 1966.
83-10-03: 83-10-03 CESSNA: Amendment 39-4655. Applies to the following airplanes certificated in any category: \n\n\nModel\nSerial Numbers \n172M\n17266940 thru 17267584\n172N\n17267585 thru 17274009\n172P\n17274010 thru 17275762, 17275764, 17275765, 17275769, 17275770, 17275788, 17275792, 17275793, 17275796, 17275798, 17275800 thru 17275803, 17275806, and 17275818\nR172K\nR1722000 thru R1723454\nF172\nF17201445 thru F17202194\nFR172\nFR17200591 thru FR17200675\n\n\tCOMPLIANCE: Required as indicated unless already accomplished. \n\n\tTo prevent possible jamming of the elevator control, accomplish the following: \n\n\ta)\tWithin the next 100 hours time-in-service, modify the right-hand control wheel yoke guide in accordance with the instructions in Cessna Single-Engine Customer Care Service Information Letter SE82-38, dated August 13, 1982, and SE82-38 Revision # 1 dated October 29, 1982. \n\n\tb)\tAirplanes may be flown in accordance with FAR 21.197 to a base where this AD may be accomplished.c)\tAn equivalent method of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building 2299, Wichita, Kansas 67209, telephone (316) 269-7000. \n\n\tThis amendment becomes effective on June 30, 1983.
2005-24-01: The FAA adopts a new airworthiness directive (AD) for all CENTRAIR 101 series gliders. This AD requires you to make pen and ink changes to the Limitations Section of the glider maintenance manual to eliminate contradictory information concerning the structural life limit. This AD results from a review by FAA of the Limitations Section of the CENTRAIR Model 101AP glider maintenance manual that revealed conflicting information concerning the structural life limit. We are issuing this AD to assure that the published life limit is adhered to and to prevent structural failure of the glider once this life limit is reached.
2018-23-12: We are adopting a new airworthiness directive (AD) for Zodiac Aero Evacuation Systems (also known as Air Cruisers Company) fusible plugs installed on emergency evacuation equipment for various transport category airplanes. This AD was prompted by reports indicating that affected fusible plugs activated (vented gas) below the rated temperature. This AD requires an inspection of the fusible plugs to determine the part number and lot number, and replacement of all affected fusible plugs. We are issuing this AD to address the unsafe condition on these products.
98-20-25: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100 series airplanes. This action requires repetitive inspections to detect cracking of the outer chord of the Body Station (BS) 1480 upper and lower bulkhead and longeron splice fitting, and repair, if necessary. Alternatively, this action requires other repetitive inspections to detect cracking of the BS 1480 upper and lower bulkhead, bulkhead outer chord, web, skin, splice components, and lower bulkhead/stringer interface; and modification of the skin splice plate, the outer chord splice fitting, and the stringer interface of the lower bulkhead, if necessary. This amendment is prompted by a report indicating that fatigue cracking was found in the outer chord of the BS 1480 bulkhead at the overwing longeron splice, and that the longeron splice fitting was completely severed. The actions specified in this AD are intended to detect and correct fatigue cracking of theBS 1480 bulkhead outer chord and longeron splice fitting, which could result in reduced structural integrity of the fuselage and the inability to carry limit load.
89-03-13: 89-03-13 SAAB-SCANIA: Amendment 39-6136. Applicability: Model SF-340A series airplanes, serial numbers -003 through -138, inclusive, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To prevent erroneous airspeed readings due to ice in the pitot system, accomplish the following: A. Install water traps and insulation pads in the main and standby pitot systems, in accordance with SAAB-Scania Service Bulletin SF340-34-056, dated August 1, 1988. 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 may add any comments and then send it to the Manager, Standardization Branch, ANM-113. C. Special flightpermits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of 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 SAAB-Scania, Product Support, S-58188, Linkoping, Sweden. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6136, AD 89-03-13) becomes effective March 15, 1989.
85-09-04: 85-09-04 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5055. Applies to Model 206L, 206L-1, and 206L-3 helicopters that have main rotor blades, Part Number (P/N) 206-015-001-001 or 206-015-001-103, with inboard trim tabs, P/N 206-015-516-101, installed. Compliance is required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible loss of the main rotor blade, accomplish the following: (a) Remove all main rotor inboard trim tabs, P/N 206-015-516-101, in accordance with Part II, paragraph A of BHTI Alert Service Bulletin 206L-85-35, dated February 26, 1985. (b) Accomplish the inspection and repair procedures as necessary in accordance with Part II, paragraphs B & C of BHTI Alert Service Bulletin 206L-85-35, dated February 26, 1985. (c) Any equivalent method of compliance with this AD must be approved by the Manager, Helicopter Certification Branch, Southwest Region, Federal Aviation Administration, P.0. Box 1689, Fort Worth, Texas 76101. (d) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the inspection and repair procedures required by this AD may be accomplished. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. This amendment becomes effective May 20, 1985.
2005-23-16: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires modification of certain wire bundles located above the center fuel tank. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent chafed wire bundles near the center fuel tank, which could cause electrical arcing through the tank wall and ignition of fuel vapor in the fuel tank, and result in a fuel tank explosion.
2018-25-15: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD was prompted by a report of cracking in the inboard lower flange and adjacent web near the forward attachment of the outboard flap track at a certain position on a Model 737-300 airplane. The flap tracks of Model 737-300 airplanes are similar to the flap tracks of Model 727 airplanes. This AD requires repetitive detailed inspections and surface high frequency eddy current (HFEC) inspections of each outboard flap track at certain positions for any crack and discrepancy, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
98-19-20: This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International CFM56-7B and -7B/2 series turbofan engines. This action requires initial and repetitive inspections of certain hydromechanical unit (HMU) overspeed governor (OSG) spool valves for out-of-specification conditions or the presence of heavy contact or galling on the spool valve, and optional installation of an improved HMU as a terminating action to the inspections. This amendment is prompted by a report of a flameout that occurred on a flight test engine due to a failed HMU OSG spool valve shaft. The actions specified in this AD are intended to prevent failure of the HMU OSG spool valve shaft, and subsequent engine flameout.
80-24-04: 80-24-04 HUGHES HELICOPTERS: Amendment 39-3979. Applies to Model 369 Series Helicopters, certified in all categories, equipped with Automatic Engine Reignition System. Compliance is required as indicated unless already accomplished. To prevent the possibility of the middle front seat occupant accidentally deactivating the Automatic Engine Reignition System and also from blocking the crew's view of the automatic reignition "ARMED" and "RE-IGN" advisory lights, accomplish the following: (a) Within thirty (30) consecutive calendar days or prior to flight in falling and/or blowing snow, whichever comes first, after the effective date of this AD, install a placard in close proximity to the Automatic Engine Reignition Arming switch and in plain view of the pilot which states "Middle front seat is not to be occupied during flight in falling and/or blowing snow" or equivalent words. (b) Special flight permits may be issued in accordance with FAR 21.197 and .199 to operate aircraft to a base for the accomplishment of modification required this AD. (c) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. This amendment becomes effective December 4, 1980.
2005-23-10: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-200 and A330-300 series airplanes; and Model A340-200 and A340-300 series airplanes. This AD requires an accelerated schedule of repetitive testing of the elevator servo control loops, and corrective actions if necessary. This AD results from reports of failed elevator servo controls due to broken guides. We are issuing this AD to ensure proper functioning of the elevator servo controls. Failure of the elevator servo controls during certain phases of takeoff could result in an unannounced loss of elevator control and consequent reduced controllability of the airplane.
2018-25-13: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000 airplanes. This AD was prompted by a report of chafing of a wire bundle located at the bottom of the right hand (RH) electrical cabinet. This AD requires a one-time general visual inspection of the wiring bundle for damage, measurement of the clearance between the metallic plate and the wiring bundle, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2018-25-11: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce Model RB211-Trent 800 engines. This AD was prompted by reports of inadequate clearance between the thermal protection system (TPS) insulation blankets and the electronic engine control (EEC) wiring, which resulted in damaged wires. This AD requires repetitive inspections of the EEC wire bundles and clips, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.