Results
2001-09-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Model A330 series airplanes. This action requires repetitive inspections of the spars, rib, and stringers in the vertical stabilizer spar box for failure of the bonds to the skin, and repair, if necessary. It also requires modification of the vertical stabilizer spar box by installation of fasteners to reinforce the bonds to the skin, which terminates the repetitive inspections. This action is prompted by issuance of mandatory continuing airworthiness information. This action is necessary to prevent failure of the bonds of the vertical stabilizer spar box to the skin, which could lead to reduced structural integrity of the spar box. It is intended to address the identified unsafe condition.
2001-08-15: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Corporation (formerly Allison Engine Company) AE 3007A, AE 3007A1/1, AE 3007A1/2, AE 3007A1, AE 3007A1/3, AE 3007A1P, and AE 3007A3 turbofan engines. This action requires initial and repetitive inspections for bearing material contamination of the engine oil system. This amendment is prompted by reports of rapid failures of the No. 1 bearing. The actions specified in this AD are intended to detect the rapid failure of the No. 1 bearing, which could result in smoke in the cabin and an uncommanded in-flight engine shutdown.
88-21-05: 88-21-05 PIPER: Amendment 39-6039. Applies to PA-60 series (all serial numbers) airplanes certificated in any category modified per Machen, Inc., Supplemental Type Certification (STC) No. SA980NM. NOTE: STC No. SA980NM pertains to installation of AVCO Lycoming Model TIO-and LTIO-540-J2BD engines. Compliance: Required as indicated, unless previously accomplished. To prevent a possible inflight engine fire, accomplish the following: (a) Within the next 50 hours time-in-service, after the effective date of this AD, and thereafter at every 100 hours time-in-service, inspect, and replace, as necessary, the exhaust systems on both engines in accordance with Machen, Inc. Service Bulletin (SB) No. 66- 018, dated June 5, 1987. (b) The repetitive inspections specified in paragraph (a) are no longer required when the exhaust system has been modified in accordance with Machen, Inc. SB 66-019, dated January 8, 1988. (c) Within the next 50 hours time-in-service, after the effective date of this AD, and thereafter at every 100 hours time-in-service, inspect, and replace as necessary the oil lines on both engines in accordance with Machen, Inc. SB 66-018, dated June 5, 1987. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent means of compliance with this AD may be used if approved by the Manager, Modification Branch, ANM-190S, FAA, Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Machen, Inc., South 3608 Davison Boulevard, Spokane, Washington 99204 or may examine these documents at the Office of the Assistant Chief Counsel, Room 1558, FAA, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-6039, becomes effective on November 6, 1988.
2016-13-08: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a report of cracking of the lower tension bolt area at the rib one junction (both sides) of the lower wing. This AD requires repetitive inspections for cracking of the fasteners and of the fitting around the fastener holes at the frame (FR) 40 lower wing location, and corrective actions if necessary. We are issuing this AD to detect and correct crack initiation of the fittings of the FR40 lower wing locations, which could result in reduced structural integrity of the airplane.
2001-08-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Model A340 series airplanes. This action requires repetitive inspections of the pivoting door roller fittings of the upper and lower thrust reversers for cracks, and corrective action, if necessary. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. This action is intended to detect and correct cracking of the pivoting door roller fittings of the thrust reversers, which could result in failure of the primary locking mechanism of the thrust reversers during flight, leading to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
87-16-12: 87-16-12 BRITISH AEROSPACE: Amendment 39-5706. Applies to Model BAe-146 airplanes, as listed in British Aerospace BAe-146 Service Bulletin 27-58, Revision 1, dated November 14, 1986, certificated in any category. Compliance is required as indicated, unless previously accomplished. To prevent an unannunciated failure of the stall identification system, accomplish the following: A. Within 14 days or prior to the accumulation of 125 landings, whichever occurs first after the effective date of this AD, inspect the electro/pneumatic solenoid valve to identify the serial number and modification state in accordance with BAe-146 Service Bulletin 27-58, Revision 1, November 14, 1986. If the valve is identified as suspect, accomplish either of the following: 1. Prior to further flight, replace the affected valve with a modified valve identified in accordance with the service bulletin; or 2. Prior to further flight, and thereafter at intervals not to exceed 14 daysor 125 landings, whichever occurs first, functionally test the suspect valve in accordance with the Accomplishment Instructions of the service bulletin. a. Valves found defective must be removed prior to further flight and replaced with modified valves or a serviceable suspect valve. b. The serviceability of suspect replacement valves must be determined by performing the above mentioned functional test upon installation. B. Replacement of suspect valves with modified valves identified in accordance with BAe-146 Service Bulletin 27-58, Revision 1, dated November 14, 1986, constitutes terminating action for the requirements of this AD. C. 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. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operateairplanes to a base for the accomplishment of the modification required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer, may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This information may be examined at 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, 39-5706, becomes effective August 31, 1987.
86-01-04: 86-01-04 HUGHES HELICOPTERS, INC. (Hughes Helicopters): Amendment 39-5187. Applies to Model 369 series helicopters including military Models YOH-6A and OH-6A, certificated in any category, equipped with tail rotor blades Part Numbers (P/N) 369A1613-3,- 7, -501, and -503, Serial Numbers (S/N) 6928 and prior; P/N's 369D21613-11, -41, and -51, S/N's 5144 and prior; P/N 369D21606, S/N's 0077 and prior; P/N 369D21615, S/N's 0480 and prior; and P/N's 421-088-BSC and -3, all serial numbers. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To prevent the loss of a tail rotor blade tip cap in flight and subsequent loss of tail rotor control, accomplish the following: (a) Remove, inspect, and modify blades in accordance with paragraphs a through g, Part I "PROCEDURE" section of Hughes Service Information Notices (SIN) DN-132.1, EN-21.1, FN-9.1, HN-199.1 dated May 1, 1985, or SIN's DN-129, EN-18,and HN-195 dated August 27, 1984. (b) An alternate method of compliance which provides an equivalent level of safety may be used when approved by the Manager of the Western Aircraft Certification Office, Hawthorne, California. (c) Special flight permits may be issued in accordance with FAR Sections 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. 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 McDonnell Douglas Helicopter Company, Centinela Avenue and Teale Street, Culver City, California 90230. These documents also may be examined at the FAA, Southwest Region, Room 158, Building 3B, 4400 Blue Mound Road, Fort Worth, Texas 76106, or at the Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California 90250. This amendment supersedes Amendment 39-4940 (49 FR 43046; October 26, 1984), AD 84-18-08. This amendment becomes effective February 14, 1986.
85-25-56 R1: 85-25-56 R1 GENERAL ELECTRIC COMPANY: Telegram issued December 20, 1985, as amended by Amendment 39-5495. Applies to General Electric Company (GE) CF6-50 and -45 series turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent failure of the left hand side seventh stage low pressure turbine (LPT) cooling air manifold tube, which could result in an LPT overtemperature condition and subsequent LPT stage 1 disk rupture, accomplish the following: (a) For those engines not in compliance with the requirements of GE Service Bulletin (SB) 75-54, dated July 19, 1985, or paragraph 2.A. or 2.B. of GE SB 75-46, Revision 3, dated June 8, 1982, comply with paragraphs (1) then (2) below: (1) Accomplish the requirements of paragraphs 2.A.1. and 2.A.2. of GE SB 75-55, dated September 13, 1985, concurrently with the requirements of paragraph 2.A. of GE SB 75-54, or FAA approved equivalents, within 10 flight cycles after the effective date ofthis AD. (2) Accomplish the requirements of paragraph 2. of GE SB 75-55 or FAA approved equivalent, within 60 calendar days of complying with paragraph (1) above. (b) For engines already in compliance with the requirements of GE SB 75-54 or paragraph 2.A. or 2.B. of GE SB 75-46, accomplish the requirements of paragraph 2. of GE SB 75-55 within 60 calendar days after the effective date of this AD. (c) Replace cracked, broken or ruptured left hand side seventh stage LPT cooling air manifold tube and attachment hardware, found during accomplishment of paragraph (a) or (b) above, before further flight. (d) Inspect the left hand side seventh stage LPT cooling air manifold tubes and attachment hardware in accordance with the requirements of paragraphs 2.A., 2.B., 2.C. and 2.D.(4)(b) of GE SB 75-58, dated April 14, 1986, or FAA approved equivalent, within the next 250 flight cycles after the effective date of this AD, and thereafter, at intervals not to exceed 250 flightcycles from the last inspection. (e) Replace or tighten, in accordance with paragraph 2.D. of GE SB 75-58, left hand side seventh stage LPT cooling air system hardware found worn, loose, cracked or broken during accomplishment of paragraph (d) above, prior to further flight. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, may adjust the compliance time specified in this AD. GE SB's 75-54, dated July 19, 1985; 75-46, Revision 3, dated June 8, 1982; 75-55, dated September 13, 1985; and 75-58, dated April 14, 1986, identified and described in this document, 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, from General Electric Company, 1 Neumann Way, Cincinnati, Ohio 45215. These documents 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 85-ANE-44, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. Paragraphs (a), (b), and (c) of this amendment become effective January 5, 1987, as to all persons except those persons to whom paragraphs (a), (b), and (c) of this amendment were made immediately effective by TAD T85-25-56, issued December 20, 1985. Paragraphs (d) and (e)of this amendment become effective January 13, 1987, as to all persons.
2016-13-12: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10, -710A2-20, and -710C4-11 turbofan engines. This AD requires removing the pawl carrier pivot pins, part number (P/N) BRR17117, from service and replacing them with parts eligible for installation. This AD was prompted by a seized low-pressure turbine (LPT) fuel shut-off pawl carrier caused by corrosion of the pawl carrier pivot pin. We are issuing this AD to prevent failure of the fuel shut-off mechanism, which could result in uncontained part release, damage to the engine, and damage to the airplane.
2001-08-18: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires installation of heat shrinkable tubing or application of Peel-Kote on each terminal connection of all cabin lighting switches in the forward and aft cabin electrical service panels. This action is necessary to prevent a short circuit within the cabin electrical service panel due to a foreign object being lodged between the terminals of a cabin light switch. Such a short circuit could result in overheating and damage to light circuits, and consequent smoke and fire in the main cabin of the airplane. This action is intended to address the identified unsafe condition.
87-06-06: 87-06-06 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5570. Applies to Lockheed Model L-1011-385 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent engine separation due to broken pylon attach fittings-to-skate-angle bolts, which are cracking because of stress-corrosion, accomplish the following: A. Before accumulating a total of 15,000 hours time-in-service or within the next 3,000 hours time-in-service after the effective date of the AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 hours time-in-service or 15 months, whichever occurs later, accomplish the following: 1. Inspect the pylon attach fittings-to-skate-angle bolts in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA approved revision. 2. If broken bolts are found, before further flight, replace each broken bolt with a new bolt in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA-approved revision. B. Before accumulating a total of 15,000 hours time-in-service or before January 15, 1991, whichever is later, replace all of the pylon attach fittings-to-skate-angle H-11 steel bolts with stress-corrosion resistant MP-35N bolts in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA- approved revision. The inspections required by paragraph A. may be discontinued after paragraph B. has been accomplished. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. D. 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 Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept. 65-33, U-33, B-1. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective April 2, 1987.
2016-13-05: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines. This AD was prompted by an uncontained failure of the high-pressure compressor (HPC) stage 8-10 spool, leading to an airplane fire. This AD requires eddy current inspection (ECI) or ultrasonic inspection (USI) of the HPC stage 8-10 spool and removing from service those parts that fail inspection. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane.
2001-08-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Aerostar Aircraft Corporation (Aerostar) Models PA-60-600, PA-60-601, PA-60-601P, PA-60-602P, and PA-60-700P airplanes. This AD requires you to replace both of the existing main landing gear lower side brace assemblies with parts of improved design. This AD is the result of several reports of cracking of the main landing gear lower side brace at the upper bolt lug discovered on preflight inspection. The actions specified by this AD are intended to correct damage or cracks in the main landing gear lower side brace at the upper bolt lug where the upper and lower side braces connect. This could result in failure of the main landing gear lower side brace. Such failure could lead to loss of control of the airplane.
2016-12-11: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report that certain center and outboard stowage bin modules were incorrectly installed. This AD requires an inspection of the center and outboard stowage bin modules for missing parts, quick release pins that are not fully engaged, and parts that are installed in incorrect locations; and corrective actions if necessary. We are issuing this AD to detect and correct incorrectly installed center and outboard stowage bin modules that might not remain intact during an emergency landing, resulting in injuries to occupants and interference with airplane evacuation.
2010-22-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Seven cases of on-ground hydraulic accumulator screw cap/end cap failure have been experienced on CL-600-2B19 aeroplanes, resulting in the loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. * * * * * * * * A detailed analysis of the calculated line of trajectory of a failed screw cap/end cap for each of the accumulators has been conducted, resulting in the identification of several areas where systems and/or structural components could potentially be damaged. Although all of the failures to date have occurred on the ground, an in-flight failure affecting such components could potentially have an adverse effect on the controllability of the aeroplane. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2016-13-04: We are adopting a new airworthiness directive (AD) for certain BRP-Powertrain GmbH & Co KG Rotax 912 F2, 912 F3, 912 F4, 912 S2, 912 S3, 912 S4, 914 F2, 914 F3, and 914 F4 reciprocating engines. This AD requires re-identification of the engine model and concurrent modification of the aircraft to indicate the maximum coolant temperature limit. This AD was prompted by a design change introduced by the manufacturer that relocated the engine cylinder head temperature sensor to a different location and converted it to a coolant temperature sensor. We are issuing this AD to prevent exceeding engine coolant temperature limits, which could result in loss of engine coolant, damage to the engine, and loss of control of the airplane.
2016-12-14: We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 170 airplanes; and all Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. This AD was prompted by reports of cracks in certain engine low-stage bleed check valves. This AD requires replacing the air management system (AMS) controller operation program of the AMS controller processor boards, and replacing the current low-stage bleed check valve and associated seals. We are issuing this AD to prevent failure of the low-stage bleed check valve; simultaneous failures of both low-stage bleed check valves could result in a dual engine in- flight shutdown.
74-22-04: 74-22-04 TELEDYNE CONTINENTAL MOTORS: Amendment 39-1998. Applies to TCM Model 6-285- B engines with engine serial numbers 700000 through 700095. Compliance required within the next 25 hours time in service after the effective date of this AD unless already accomplished. Inspect the crankcase main bearing oil supply passages in accordance with procedures outlined in Teledyne Continental Service Bulletin M74-21. After compliance with this bulletin, if it is determined that an oil passage has been omitted the engine must be removed from service. This amendment becomes effective October 28, 1974.
97-02-12: 97-02-12 ROLLS-ROYCE PLC: Amendment 39-9897. Docket 96-ANE-09. Applicability: Rolls-Royce plc. (R-R) Models RB211-535E4 and -535E4-B turbofan engines installed on Boeing 757-200 series aircraft. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent compressor stall and subsequent engine rundown on one or both engines, accomplish the following: (a) No later than 9 calendar months after the effective date of this AD, install a fuel flow governor (FFG) that incorporates a revised minimum compressor discharge P4 stop setting, in accordance with R-R Mandatory Service Bulletin (SB) No. RB.211-73-B869, Revision 1, dated May 24, 1996. (b) Installation of improved FFGs on both engines for each Boeing 757 aircraft in accordance with paragraph (a) of this AD constitutes terminating action to the requirements of AD 96-04-11. (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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (e) The actions required by this AD shall be done in accordance with the following R-R Mandatory SB: Document No Pages Revision Date RB.211-73-B869 1-4 1 May 24, 1996 5-9 Original February 12, 1996 Supplement 1 Original February 12, 1996 Total Pages: 10. 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 Rolls-Royce plc, P.O. Box 31, Moor Lane, Derby, DE248BJ, United Kingdom; telephone 1332-249428, fax 1332-249423. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (f) This amendment becomes effective on April 4, 1997.
64-21-06 R2: 64-21-06 R2 BOEING VERTOL: Amendment 813 Part 507 Federal Register September 10, 1964 as amended by Amendment 39-2156 is further amended by Amendment 39-3827. Applies to Model 107-II helicopters. Compliance required as indicated. As a result of a fatigue failure in service of the rotor pitch housing, accomplish the following: (a) Unless already accomplished within the last 30 hours' time in service, before further flight, inspect the lug areas of all rotor pitch housings P/N's 107R2553-1, -2, -3, -4, -5, and -6 and blade sockets P/N's 42R1043-7 and -8 with 260 or more hours' time in service using magnetic particle inspection method or FAA approved equivalent. To accomplish the inspection, remove rotor blades and rotor hub pitch bearing assemblies. Repeat this inspection at intervals not to exceed 30 hours' time in service. (b) Inspect, using magnetic particle inspection, the lug areas of all rotor pitch housings P/N's 107R2553-1, -2, -3, -4, -5, and -6 and blade sockets P/N's 42R1043-7 and -8 with less than 260 hours' time in service in accordance with (a) prior to the accumulation of 260 hours' time in service. (c) Conduct a daily visual inspection for cracks in the lug areas of all rotor pitch housings P/N's 107R2553-1, -2, -3, -4, -5, and -6 and blade sockets P/N's 42R1043-7 and -8. This may be accomplished without disassembly from the helicopter. (d) Unless already accomplished, within the next 50 hours in service on pitch housing 107R2553-8, -10, -14, -16, with 1000 hours or more in service and within the next 100 hours in service on pitch housing 107R2553-7, -9, -13, 15, with 2000 hours or more in service install crack detector wire in accordance with Part I "Installation Procedure" of Boeing Service Bulletin No. 107-343 dated March 10, 1980, or equivalent. (1) Inspect for cracks in accordance with Part II "Inspection Procedures" of the above Bulletin, or equivalent, the lug area of pitch housings 107R2553-8, -10, -14, -16 with 1000 hours or more in service within the next 50 hours in service and thereafter at intervals not to exceed 25 hours in service, and pitch housing 107R2553-7, -9, -13, -15 with 2000 hours or more in service within the next 100 hours in service and thereafter at intervals not to exceed 50 hours in service. (2) Unless already accomplished, install crack detector wire in accordance with Part I "Installation Procedure" of the above Bulletin, or equivalent on pitch housings 107R2553-8, -10, -14, -16 with less than 1000 hours in service prior to the accumulation of 1050 hours in service, and on pitch housings 107R2553-7, -9, -13, -15 with less than 2000 hours in service prior to the accumulation of 2100 hours in service. (3) Inspect pitch housings 107R2553-8, -10, -14, -16 with less than 1000 hours in service in accordance with (1) prior to accumulation of 1050 hours in service. Inspect pitch housings 107R2553-7, -9, -13, -15 with less than 2000 hours in service in accordance with (1) prior to accumulation of 2100 hours in service. (4) Conduct a visual inspection for cracks in the lug area of blade sockets 42R1043-11, -12, -13 and -14 at intervals not to exceed 50 hours in service. This may be accomplished without disassembly from the helicopter. (e) If any cracks are found replace the part before further flight with a part found serviceable in accordance with this AD. (f) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance times specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (g) Retire from service all rotor pitch housings P/N's 107R2553-7, -8, -9, -10, -13, - 14, -15, d -16 upon the accumulation of 5,000 hours' total time in service. This supersedes AD 64-06-08. Amendment 39-813 was effective September 10, 1964. Amendment 39-2156 was effective April 9, 1975. This Amendment 39-3827 is effective July 7,1980.
60-12-01: 60-12-01 CONTINENTAL: Amdt. 153, Part 507, Federal Register May 17, 1960. Applies to E185-8, E185-9, E185-11, E225-4 and E225-8 Engine Models. Compliance required at next periodic inspection, but not later than September 1, 1960. An inflight failure has indicated that additional information regarding engines affected by replacement requirements of AD 56-06-01 should be provided. This AD is therefore issued to supply specific serial numbers of engines that were rebuilt (remanufactured) between April 1, 1954 and May 1, 1955. The affected engines are: Remanufactured E185-8, -9 and -11 Engines: 25015, 25037, 25044, 25048, 25057, 25065, 25071, 25075, 25086, 15087, 25137, 25141, 25162, 25189, 25202, 25210, 25220, 25234, 25243, 24254, 25269, 25288, 25307, 25320, 25325, 25333, 25376, 25379, 25381, 25387, 25422, 25426, 25464, 25518, 25526, 25545, 25562, 25575, 25578, 25611, 25649, 25718, 25754, 15761, 25766, 25767, 25783, 25790, 25795, 25819, 25834, 25897, 25930, 25950, 25957, 25958, 26003, 26088, 26095, 26104, 26121, 26138, 26304, 26321, 26327, 26343, 26352, to 26412 inclusive. Remanufactured E225-4 and -8 Engines: 30122, 30391, 30454, 32154, 35001, 35082, 35086, 35095, 35113, 35128, 35132, 35133, 35135, 35137, 35138, 35139, 35144, 35145, 35151, to 35254 inclusive. The above engines may have piston pin assembly P/N 530845, which is satisfactory, or piston pin assembly P/N 535145, which is unsatisfactory. Unless previously accomplished per Continental Service Bulletin No. M56-2 dated February 14, 1956, including Supplement No. 1 dated March 12, 1956, or AD 56-06-01, replace piston pin assembly P/N 535145 with P/N 539467. Use the applicable method of inspection outlined below to determine which piston pin assembly is installed in the above remanufactured engines: (a) If none of the cylinders on the engine in question have been removed in the field since the engine was shipped from the factory, remove and inspect the piston pin assembly in any one of the cylinders. Continental Motors Corporation procedures provide that all cylinders will have the same piston pin assembly. (b) If the engine in question has had any of the cylinders removed in the field since the engine was shipped from the factory, inspect those cylinders and also at least one of the factory installed cylinders which has not been disturbed. This supplements AD 56-06-01 and supersedes AD 59-10-04.
85-22-08 R2: 85-22-08 R2 GATES LEARJET CORPORATION: Amendment 39-5166 as amended by Amendment 39-5223 is further amended by Amendment 39-5296. Applies to Model 55 airplanes, serial numbers 55-003 through 55-086, except those incorporating Service Bulletin 55- 27-7A, Airplane Modification Kit 55-84-7B, or Airplane Accessory Kit 55-83-4. Compliance required as indicated after the effective date of this AD, unless already accomplished. To prevent use of incorrect landing distances, accomplish the following: A. Within the next 10 hours time-in-service after the effective date of this AD, insert the following information in the "FAA Approved Airplane Flight Manual for Gates Learjet 55," dated 3/17/81 (on 10/4/85, changes through Change 20, dated 5/10/84, were current): 1. Replace the paragraph "SPOILERS/AUTOSPOILERS/ SPOILER0NS" (pages 1-14) with: "SPOILERS/SPOILERONS (a) Spoilers (1) During landings, a time delay in the spoiler circuit will cause increased spoiler extension times. For a normal landing (spoilerons operative with flaps below 25 degrees), full spoiler extension will require approximately 5 seconds. If the spoilerons are inoperative (AUG AlL light illuminated) or the SPOILER0N circuit breaker (co-pilot's AC bus) is pulled, spoiler extension will require approximately 11 seconds. To account for the increase spoiler deployment times, the following corrections must be applied to the Actual Landing Distance obtained from the ACTUAL LANDING DISTANCE chart in Section V: Normal Landing: Multiply distance by 1.04. Spoilerons Inoperative: Multiply distanced 1.15. (2) If the spoilers are inoperative during flight, the maximum operating altitude is limited to 41,000 feet. (3) Do not extend spoilers with flaps extended while airborne. (4) Do not extend spoilers, or operate with spoilers deployed, at speeds above VM0/MM0. (b) Spoilerons (1) Spoilerons may be inoperative. If spoileron preflight check fails, the SP0ILERON circuit breaker (co-pilot's AC bus) must be pulled. When the SP0ILERON circuit breaker is pulled, the spoilers and spoilerons will be inoperative in flight and landing spoiler deploy times will increase. With spoilerons inoperative, the maximum operating altitude will be limited to 41,000 feet, and the Actual Landing Distance obtained from Section v must be increased by 15 percent (multiply by 1.15)." 2. Replace the first NOTE under the BEFORE TAXI Spoileron System Check (page 2-20) with the following: "In the event the spoilerons fail the following check, SP0ILERON circuit breaker (co-pilot's AC bus) - Pull. AUG AlL will illuminate. The spoilers and spoilerons will be inoperative in flight. The spoiler deploy time will be increased for landing. In this event, the maximum operating altitude is limited to 41,000 feet and the Actual Landing Distance obtained from Section V must be increased 15 percent (multiply by 1.15)." 3. The following factors must be applied to the Actual Landing Distance obtained from figure 5-57 (page 5-74): "Normal Landing: Multiply distance by 1.04 Spoilers Inoperative: Multiply distance by 1.15." B. In order to comply with the requirements of paragraph A., above, a copy of this AD may be used as a temporary amendment to the Airplane Flight Manual (AFM) and carried in the airplane as part of the AFM until replaced by Gates Learjet-published Temporary Flight Manual (TFM) Changes TFM 85-17, TFM 85-18, and TFM 85-19. C. Temporary Flight Manual (TFM) Changes TFM 85-17, TFM 85-18, and TFM 85-19 may be removed from the AFM upon incorporation of either Gates Learjet Service Bulletin (SB) 55-27-7A (dated December 12, 1985), Airplane Modification Kit (AMK) 55-84-7B (dated December 12, 1985), or Airplane Accessory Kit (AAK) 55-83-4. D. For airplanes equipped with thrust reversers modified in accordance with Gates Learjet SB 55-27-7 or AMK 55-84-7A, that modification (SB 55-27-7 or AMK 55-84-7A) must be removed within the next 30 days after the effective date of this AD. E. For airplanes not equipped with thrust reversers, modification in accordance with Gates Learjet SB 55-27-7 or AMK 55-84-7A constitutes terminating action for the requirements of this AD. F. Alternate means of compliance with provide an acceptable level of safety may be used when approved by the Manager, Wichita Aircraft Certification Office, FAA, Central 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 Gates Learjet Corporation, P.0. Box 7707, Wichita, Kansas 67277. These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas. Amendment 39-5166 became effective November 22,1985. Amendment 39-5223 became effective February 6, 1986. This Amendment 39-5296 becomes effective May 19, 1986.
2016-12-13: We are superseding Airworthiness Directive (AD) 2000-05-17 and AD 2001-04-12, which apply to Eurocopter France (now Airbus Helicopters) Model EC120B helicopters. AD 2000-05-17 and AD 2001-04-12 required repetitive visual checks of the engine-to-main gearbox (MGB) coupling tube assembly (coupling tube) for a crack and replacing any cracked tube with an airworthy tube. This new AD requires removing certain engine mount parts from service, measuring the height of the engine mounting base for certain helicopters, replacing the engine mount if a certain height is exceeded, inspecting the flared coupling on certain helicopters for a crack, and replacing the coupling if it is cracked. Since we issued AD 2000-05-17 and AD 2001-04-12, there have been reports of additional cracks in coupling tubes. These actions are intended to prevent coupling tube failure, loss of engine drive, and a subsequent forced landing of the helicopter.
2016-12-15: We are superseding Airworthiness Directive (AD) 2016-07-30 for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes, and all Airbus Model A340-200, -300, -500, and -600 series airplanes. For certain airplanes, AD 2016-07-30 required replacing certain Angle of Attack (AOA) sensors (probes) with certain new AOA sensors. For certain other airplanes, AD 2016-07-30 also required inspections and functional heat testing of certain AOA sensors for discrepancies, and replacement if necessary. This new AD requires the same actions as AD 2016-07-30. This new AD was prompted by a report of a typographical error in the regulatory text of AD 2016-07-30. We are issuing this AD to prevent erroneous AOA information and Alpha Protection (Alpha Prot) activation due to blocked AOA probes, which could result in a continuous nose-down command and consequent loss of control of the airplane.
2016-12-12: We are superseding Airworthiness Directive (AD) 2008-05-18 R1 for certain Fokker Services B.V. Model F.27 Mark 050, 200, 300, 400, 500, 600, and 700 airplanes. AD 2008-05-18 R1 required revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This new AD requires a new maintenance or inspection program revision to incorporate the revised Airworthiness Limitation Items (ALIs) and critical design configuration control limitations (CDCCLs). This new AD also adds certain airplanes to the applicability. This AD was prompted by the issuance of revised service information to update the Fuel ALIs and CDCCLs that address fuel tank system ignition sources. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.