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63-18-01: 63-18-01 CANADAIR: Amdt. 608 Part 507 Federal Register August 22, 1963. Applies to all Model CL-44D4 aircraft. Compliance required as indicated. As a result of failure of an elevator hinge bolt the following must be accomplished: (a) Within 50 hours' time in service from the effective date of this AD, unless already accomplished, replace the elevator station 299 hinge bolt aluminum locking plate with both a steel locking plate and a steel hinge bolt retainer in accordance with Canadair Service Bulletin CL44D4-302 or FAA approved equivalent. (b) Within 250 hours' time in service from the effective date of this AD, unless already accomplished, replace the elevator hinge bolt aluminum locking plates at Stations 84, 174.9, and 181 with steel locking devices in accordance with Part A of Canadair Service Bulletin CL44D4-316, or FAA approved equivalent. Compliance time for incorporating this modification may be increased to 500 hours provided the hinges are inspected in accordance with (c) within 250 hours' time in service from the effective date of this AD. (c) Within 250 hours' time in service after installing the steel locking plate or device, and thereafter within 250 hours' time in service from the last inspection, inspect for damage the elevator hinge bolt head, bolt locking plate, and bolt retainer at Stations 84, 174.9, 181, and 299. Damaged parts must be replaced before further flight. (d) For aircraft incorporating horizontal stabilizers conforming to Canadair Modification Summary No. 44-502, or modified in accordance with Canadair Service Bulletin CL44D4-243, perform the special inspections of Canadair Service Information Circular No. 180- CL44D4, Issue No. 5, or subsequent FAA approved issues, within 250 hours' time in service from the effective date of this AD, and thereafter at the intervals noted in the Circular for particular inspections. (e) For aircraft incorporating horizontal stabilizers which do not conform to Canadair Modification Summary No. 44-502, or which have not been modified in accordance with Canadair Service Bulletin No. CL-44D4-248 accomplish the following: (1) Perform the special inspections of Canadair Service Information Circular No. 60-CL44D4, Issue 6, or subsequent FAA approved issues, at the intervals noted therein for particular inspections. Part (a) of Circular No. 60-CL44D4 must be initially performed within 35 hours' time in service from the effective date of this AD and Part (b) must be initially performed within 250 hours' time in service from the effective date of this AD. (2) Inspect for damage all elevator hinge support structure and attachment fittings on the rear face of the horizontal stabilizer rear spar at Stations 84, 174.9, 181, and 299, within 250 hours' time in service from the effective date of this AD and thereafter within 250 hours from last inspection. Damaged parts must either be replaced or repaired in accordance with an FAA approved repair procedurebefore further flight. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, International Engineering and Manufacturing Branch, International Division, Washington 25, D.C., may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This directive effective September 22, 1963.
2015-03-01: We are adopting a new airworthiness directive (AD) for all Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of dislodged engine fan cowl panels. This AD requires installing additional attaching hardware on the left and right fan cowl access panels and the nacelle attaching structures. We are issuing this AD to prevent damage to the fuselage and flight control surfaces from dislodged engine fan cowl panels.
60-07-03: 60-07-03 CALLAIR: Amdt. 119 Part 507 Federal Register March 25, 1960. Applies to All CallAir Models A-4, A-4 Modified, A-5 Up To and Including Serial Number 292 and A-6 Aircraft Serial Numbers 202, 244, 248, 252, 262, 264, 268, 269, 270 and 271. Compliance required not later than May 15, 1960, and at each 50 hours' time in service thereafter. Due to reports of cracks and separation of the lower diagonal brace member on the engine mount the following inspection shall be conducted. Visually inspect the lower diagonal brace member of the engine mount especially in the area of the gusset plates at the ends of the members. If cracks are found, replace with CallAir redesigned mount, P/N 6-11-4A, or repair in accordance with the method outlined in CallAir Service Bulletin No. 7, or equivalent. After replacement with P/N 6-11-4A or repair, this special inspection may be discontinued. (CallAir Service Bulletin No. 7 covers this same subject.)
81-01-51: 81-01-51 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4052. Applies to Models SA360C, SA365C, SA365C1 and SA365C2 helicopters, certificated in all categories, which do not have Aerospatiale modification AMS 365A.07.2457 incorporated. Compliance required as indicated. To prevent failures of the tail boom or fin due to fatigue cracking at Frame 9420 accomplish the following unless already accomplished: (a) For helicopters which have 20 hours' or more total time in service on the effective date of this AD, inspect in accordance with paragraph (c) within 5 hours' time in service. (b) For those helicopters which have less than 20 hours' total time in service on the effective date of this AD, inspect in accordance with paragraph (c) before reaching 25 hours' time in service. (c) Inspect for cracks in the outer fairing connecting the fin base leading edge to the tail boom within the transmission shaft passage area at Frame 9420 using the visual method in accordance with Aerospatiale SA360/365 Service Bulletin Number 05.04 dated November 20, 1980, or an FAA-approved equivalent and comply with paragraphs (d), (e), or (f) of this AD as appropriate. (d) If no cracks are found as a result of the inspection required in paragraph (c) of this AD, return the helicopter to service and repeat the inspection required in paragraph (c) at intervals not to exceed 25 hours' time in service since the last inspection. (e) If a crack is found as a result of the inspections required in paragraph (c) of this AD that is less than 2 inches (50 mm) long, the helicopter may be returned to service and the inspection required in paragraph (c) of this AD must be done after the last flight of each day. (f) If a crack is found as a result of the inspections required in paragraph (c) of this AD that is 2 inches (50 mm) or more in length, incorporate Aerospatiale modification AMS 365A.07.2457 or an equivalent noted in paragraph (g) before furtherflight. (g) The inspections required in paragraph (c) may be discontinued when Aerospatiale modification AMS 365A.07.2457 is incorporated. Equivalent modifications may be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. NOTE: Aerospatiale SA360/SA365 Service Bulletin Number 53.09 dated November 2, 1980, refers to this modification. This amendment becomes effective February 28, 1981, to all persons except those persons to whom it was made immediately effective by telegraphic AD T81-01-51, issued December 31, 1980, which contained this amendment.
62-03-03: 62-03-03 NAVION: Amdt. 396 Part 507 Federal Register February 3, 1962. Applies to Navion, Navion A, B, D, E, F, and G Aircraft. Compliance required within the next 25 hours' time in service after the effective date of this AD and at each periodic inspection thereafter. The landing gear selector valve end fitting P/N 145-58145-3 (heat treated and non-heat treated) has a service history of failure during attempts to extend the gear. To preclude further difficulties: Inspect the gear actuating system in accordance with Navion Service Letter No. 81, dated March 31, 1961. Any defective parts found as a result of this inspection must be replaced prior to further flight. This supersedes AD 50-24-01. This directive effective March 6, 1962.
2015-02-02: We are adopting a new airworthiness directive (AD) for certain [[Page 5903]] Bombardier, Inc. Model CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes. This AD was prompted by a report that, during a routine inspection, corrosion was discovered on the lower bearing of the rudder upper torque tube. This AD requires applying grease to the bearing; doing a general visual inspection of the expelled old grease for any contaminants, metal wear, and indication of corrosion, and replacing the bearing if necessary; and revising the maintenance or inspection program, as applicable, to incorporate the rudder spring tab operational test and a check of the rudder spring tab operation into the daily inspection. We are issuing this AD to prevent corroded bearings, which could result in a partial or total loss of axial support.
83-16-51: 83-16-51 BOEING VERTOL COMPANY: Amendment 39-4741. Applies to Boeing Vertol Model 234 series helicopters certificated in all categories. Compliance is required as indicated (unless already accomplished). To prevent possible hazards in flight associated with damage or loss of main rotor blade tip cap and weights, accomplish the following: (a) Prior to further flight on helicopters equipped with main rotor blades with less than 100 hours time in service, conduct a borescope inspection of the inside root end of the spar for excessive potting material. It will be necessary to remove the tip cap to conduct this inspection. Remove any cracked potting material or any potting material in excess of one cubic inch. Remove any excess potting material in accordance with Boeing Vertol Service Bulletin No. 234621004 dated July 27, 1983, or FAA approved equivalent. less than 500 hours time in service, conduct the inspection and removal of material as stated in paragraph (a) within the next 30 hours time in service. (c) For main rotor blades with 500 or more hours time in service conduct the inspection and removal of material as stated in paragraph (a) within the next 75 hours time in service. (d) An equivalent method of compliance with this AD may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581. This amendment becomes effective October 26, 1983, as to all persons except those persons to whom it was made immediately effective by telegraphic AD No. T83-16-51 issued August 4, 1983, which contained the amendment.
60-11-06: 60-11-06 LYCOMING: Amdt. 162 Part 507 Federal Register May 27, 1960. Applies to GO-480-C, -G and All GSO-480 Series Engines. Compliance required at first engine overhaul after July 1, 1960. To prevent excessive crankshaft counterweight bushing wear and subsequent detuning of the counterweights, crankshafts with cast counterweights must be modified to incorporate forged counterweights with hardened steel counterweight bushings. (Lycoming Service Bulletin No. 249A covers this same subject.)
64-26-01: 64-26-01\tBOEING: Amdt 830 Part 39 (New) Federal Register November 18, 1964. Applies to Model 727 Series Aircraft. \n\n\tCompliance required as indicated. \n\n\t(a)\tBefore further flight after the effective date of this AD, open the SP-50 autopilot roll and pitch d.c. circuit breakers on panel P-18. \n\n\t(b)\tAt the first scheduled stop where facilities and personnel are available secure these circuit breakers in the off position. \n\n\t(c)\tAutopilot may be reactivated when modified in accordance with Boeing Service Bulletin 22-7 dated October 27, 1964, or an FAA Western Region Aircraft Engineering Division approved equivalent. \n\n\tThis directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated October 23, 1964.
2015-02-04: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model MYSTERE-FALCON 50 airplanes. This AD was prompted by a report of an untimely and intermittent indication of slat activity due to chafing of the electrical wiring under the glare shield and behind the flight deck front panel. This AD requires installing two protective plates between the electrical wiring under the glare shield and the engine fire pull handles. We are issuing this AD to prevent chafing of the electrical [[Page 5035]] wiring, which could result in a short circuit and generation of smoke in the cockpit, potential loss of several functions essential for safe flight, and consequent reduced controllability of the airplane.
65-10-01: 65-10-01 FAIRCHILD: Amdt. 39-64 Part 39 Federal Register May 8, 1965. Applies to Model F-27 Aircraft with Center Hinge Wing Flap Asymmetry Switches, P/N 658-001. Compliance required within 25 hours' time in service after the effective date of this AD, unless already accomplished. (a) Modify aircraft in accordance with Fairchild Service Bulletin No. 27-19, dated June 6, 1960, or Service Bulletin No. 27-26, dated September 9, 1960, Revision 1, dated March 1, 1965, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request of an operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the compliance time specified in this AD if the request contains substantiating data to justify the increase for such operator. This directive effective upon publication in the Federal Register for all persons except those to whom it was madeeffective immediately by telegram dated April 23, 1965.
60-01-06: 60-01-06 LOCKHEED: Amdt. 85 Part 507 Federal Register January 16, 1960. Applies to All Model 188A and 188C Aircraft Except Serial Numbers: 1001, 1044, 1088, 1090 and Up, For the Wing Station 167 Area Inspections; 1001, 1044, 1057, 1066, 1068 and Up, For the Wing Station 209 Area Inspections. Compliance with the following is required. (a) A daily visual inspection of the No. 4 left and right upper wing surface planks for spanwise cracks. The affected areas are adjacent to the Nos. 2 and 3 nacelle attach angles above wing Stations 167 and 209 main landing gear ribs and near the forward edge of the plank. This inspection may be discontinued when an approved reinforcement designed to prevent cracking is installed.* (b) If cracks are found, FAA approved repair and reinforcement must be accomplished(*) prior to the operation of the aircraft except that the aircraft may be ferried to the base at which the repairs and reinforcement may be performed. Upon installation of an approved reinforcement and repair the aircraft may be returned to service, and the daily inspection discontinued.** (c) An approved reinforcement shall be installed prior to February 1, 1960. This supersedes AD 59-16-06. *Lockheed Service Bulletin No. 88/SB-306 contains an approved reinforcement for the wing Station 209 area. **Eastern Air Lines sketches 62059 and 62259, revised June 25, 1959, contain an approved reinforcement and repair in the wing Station 299 area. Lockheed sketch ALS 82959, Change A, contains an approved reinforcement and repair for the wing Station 167 area.
83-07-24: 83-07-24 BOEING: Amendment 39-4630. Applies to Boeing Model 767 Airplanes VA006- VA012, VA302-VA306, VA501-VA503, VA701-VA702, VA801-VA802, and VA805. To prevent degradation of cargo compartment fire protection system effectiveness, accomplish the following, unless already accomplished.\n \n\tA.\tWithin 30 days after the effective date of this AD, inspect all forward and aft cargo compartment drain valves and rework, if necessary, in accordance with Boeing Service Bulletin 767-51-1 dated January 14, 1983, or later FAA approved revision. \n\n\tB.\tAircraft may be operated after the 30 day compliance period if the inspection has not been completed, provided no cargo is carried in the affected cargo compartments. \n\n\tC.\tAlternate 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. \n\n\tD.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the above specified Service Bulletin from the manufacturer may obtain copies upon request to The Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124, or it may also be examined at FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective April 25, 1983.
2015-02-01: We are superseding airworthiness directive (AD) 2011-23-01 for all Technify Motors GmbH (TMG) models TAE 125-01 and TAE 125-02-99 reciprocating engines with certain part number (P/N) and serial number (S/N) clutch assemblies installed. AD 2011-23-01 required replacement of certain P/N and S/N clutch assemblies. This AD requires the same actions but [[Page 4765]] expands the population of affected P/N and S/N clutch assemblies. This AD was prompted by an additional report of a clutch assembly that malfunctioned due to disk springs that received a nonconforming heat treatment process. We are issuing this AD to prevent failure of the clutch assembly, which could lead to failure of the engine, in-flight shutdown, and loss of control of the airplane.
80-18-02: 80-18-02 GROUPEMENT d'INTERET ECONOMIQUE (AIRBUS INDUSTRIE): Amendment 39-3899. Applies to Model A300 series airplanes, certificated in all categories. Compliance is required as indicated. To prevent incorrect pitch trim control operation which could result in pitch trim control runaway and possible loss of control of the airplane, accomplish the following: (a) Before each flight, check the pitch trim system in accordance with the instructions in paragraph 2, "ACCOMPLISHMENT INSTRUCTIONS," of Airbus Industrie Service Bulletin No. A300-22-024, Revision No. 4, dated August 30, 1976, or an FAA-approved equivalent, on airplanes in which the modifications required by paragraph (b) of this AD have not been incorporated. (b) Within the next 750 hours time in service after the effective date of this AD, unless already accomplished, modify the trim handwheel and the wiring between the electronic rack 80VU/STA 1380 and the flight compartment overhead panel, and replace the trim engage unit in accordance with the instructions in paragraph 2, "ACCOMPLISHMENT INSTRUCTIONS," of Airbus Industrie Service Bulletin No. A300-22-025, Revision No. 4, dated May 23, 1979, or an FAA-approved equivalent. (c) After accomplishing the modifications required by paragraph (b) of this AD, comply with the following: (1) At intervals not to exceed 2,000 hours time in service from the last inspection, perform the operational inspection in accordance with paragraph 3.A. of Airbus Industrie Service Bulletin No. A300-22-025, Revision No. 4, dated May 23, 1979, or an FAA- approved equivalent. (2) At intervals not to exceed 6,000 hours time in service from the last inspection, perform the functional inspection in accordance with paragraph 3.B of Airbus Industrie Service Bulletin No. A300-22-025, Revision No. 4, dated May 23, 1979, or an FAA-approved equivalent. (d) After the modifications required in paragraph (b) of this AD have been accomplished, compliance with paragraph (a) of this AD is no longer required. (e) If an equivalent means of compliance is used in complying with paragraphs (a), (b), and (c), that equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. This amendment becomes effective September 4, 1980.
2014-25-51: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires revising the airplane flight manual to advise the flightcrew of emergency procedures for abnormal Alpha Protection (Alpha Prot). This AD was prompted by a report of Angle of Attack (AoA) probes jamming on an in-service Airbus Model A321 airplane. Jamming of the two AoA probes during climb is attributed to water freezing under the AoA vane slinger, and led to activation of the Alpha Prot while the Mach number increased, which resulted in an airplane pitch down per design. We are issuing this AD to ensure that the flightcrew has procedures to counteract the pitch down order due to abnormal activation of the Alpha Prot. An abnormal Alpha Prot, if not corrected, could result in loss of control of the airplane.
T84-18-51: T84-18-51 BELL HELICOPTER TEXTRON, INCORPORATED: Telegram issued September 7, 1984. Applies to Bell Helicopter Textron, Incorporated, Model 214ST helicopters certified in all categories that are equipped with main rotor spindles P/N 214-010-103-003 (Airworthiness Docket No. 84-ASW-42). Compliance is required as indicated. To prevent possible failure of the main rotor spindles, accomplish the following: A. Remove from service any spindle with 1250 or more hours time in service on October 15, 1984, and thereafter at intervals not to exceed 1250 hours time in service. B. After the effective date of this AD, for aircraft with spindles which have, or attain, 1250 or more hours time in service, perform a daily inspection of the main rotor spindle as prescribed in Bell Alert Service Bulletin 214ST-84-24 or other FAA approved equivalent procedure. Remove any cracked spindle from service and replace with a serviceable spindle. C. After the effective date of thisAD, replace all spindles having, or attaining 1250 or more hours time in service, within the next 150 hours time in service or October 15, 1984, whichever occurs first. D. The helicopter may be flown to a repair base for the above inspection under the provisions of FAR 21.197. E. Any equivalent means of compliance with this AD must be approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, Southwest Region. F. Bell Helicopter Textron, Incorporated, Telegraphic Alert Service Bulletin 214ST- 84-23 is an equivalent means of compliance with this AD. This airworthiness directive becomes effective upon receipt.
84-03-07: 84-03-07 McDONNELL DOUGLAS: Amendment 39-4807. Applies to McDonnell Douglas Model DC-10 and KC-10A (Military) series airplanes, incorporating a horizontal stabilizer single chain differential drive system, certificated in all categories. Compliance required within 6 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent uncommanded movement of the horizontal stabilizer following fused drive system shear pin failure, accomplish the following: \n\n\tA.\tModify the horizontal stabilizer drive assembly in accordance with Section 2, Accomplishment Instructions, of McDonnell Douglas DC-10 Service Bulletin 27-192, Revision 1, dated August 1, 1983, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: No additional work is required for those operators who accomplished the original issue of McDonnell Douglas DC-10 Service Bulletin 27-192, dated March 17, 1983. \n\n\tB.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. \n\n\tC.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also 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. \n\n\tThis amendment becomes effective March 19, 1984.
2014-26-04: We are adopting a new airworthiness directive (AD) for certain GROB-WERKE Models G115EG and G120A airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 a defective starter solenoid. We are issuing this AD to require actions to address the unsafe condition on these products.
80-03-10: 80-03-10 MCDONNELL DOUGLAS: Amendment 39-3673. Applies to Model DC-10, -10F, -30, -30F, -40 series airplanes certificated in all categories. \n\n\tCompliance is required as indicated. \n\n\tTo reduce the probability of complete failure of the stall warning function, accomplish the following: \n\n\t(a)\tOn or before 210 days after the effective date of this AD, unless already accomplished: \n\n\t\t1.\tInstall two (2) auto throttle/speed control computers, each of which receives information from the positions of both outboard wing slat groups, in addition to other previously required inputs, in accordance with design data approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t\t2.\tInstall a stick shaker at the First Officer's position, in addition to that previously required at the Captain's position, with both stick shakers actuated by either auto throttle/speed control computer in accordance with design data approved by the Chief, Aircraft Engineering Division, FAAWestern Region. \n\n\t(b)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of modifications required by this AD. \n\n\t(c)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective February 21, 1980.
2014-26-01: We are adopting a new airworthiness directive (AD) for Alpha Aviation Concept Limited Model R2160 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 paint adherence defects inside the engine air intake box and cohesion defects inside the laminated ducting from the filter to the air intake box. We are issuing this AD to require actions to address the unsafe condition on these products.
79-11-03: 79-11-03 PRATT & WHITNEY AIRCRAFT OF CANADA: Amendment 39-3477. Applies to Pratt & Whitney Aircraft of Canada, Limited PT6T-3 power sections prior to serial number CP-PS 61324 and PT6T-6 power sections prior to serial number CP-PS 72321. Compliance required within the next 3000 hours in service after the effective date of this AD, unless already accomplished. To preclude automatic fuel control contamination install the P3 air filter and associated parts in accordance with Paragraph 2, Accomplishment Instructions in Pratt & Whitney Aircraft of Canada, Ltd. Engine Service Bulletin No. 5124 thru Revision 3 or approved equivalent procedures and parts. Equivalent procedures and parts must be approved by the Chief, Engineering and Manufacturing Branch of the Eastern Region of the Federal Aviation Administration (FAA). This amendment is effective May 31, 1979.
62-11-01: 62-11-01 GENERAL ELECTRIC: Amdt. 434 Part 507 Federal Register May 3, 1962. Applies to All CJ805-3, -3A, and -3B Engines Equipped With GE P/N 105R684P5 or 105R684P6 Thrust Reverser Actuating Pumps. Compliance required at next engine overhaul. Instances of thrust reverser pump failure have occurred causing the reverser to be inoperative and resulting in asymmetric power conditions upon application of reverse thrust during the aircraft landing roll. To correct this unsafe condition replace reverser pumps GE P/N's 105R684P5 and 105R684P6 with GE P/N 105R684P10 reverser pump, or modify the reverser pumps to conform to the P/N 105R684P10 by reducing the width of the pump drive gears and enlarging the size of the pump shaft oil seal vent in accordance with GE Service Bulletins Nos. (3B)78-1 and (3)78-16. Pumps so modified shall be reidentified as P/N 105R684P10. This directive effective June 4, 1962.
79-10-10: 79-10-10 AYRES CORPORATION (FORMERLY ROCKWELL INTERNATIONAL AND SNOW AERONAUTICAL COMPANY): Amendment 39-3469. Applies to all Ayres S-2D and S-2R airplanes certificated in all categories having installed the rudder assembly with the single upper hinge (P/N 54030-87). This AD does not apply to S-2D and S-2R airplanes which have installed a rudder assembly with three upper hinges. \n\n\tCompliance is required as indicated unless already accomplished. \n\n\tTo prevent the possible separation of the single upper hinge from the rudder assembly and consequent possible loss of airplane directional control, accomplish the following: \n\n\tWithin 10 hours' time in service after the effective date of this AD, and at intervals not to exceed 100 hours' time in service and thereafter on all S-2D and S-2R airplanes having an installed rudder assembly with a single upper hinge (P/N 54030-87), perform the visual repetitive inspection in accordance with procedures listed in paragraph 1. \n\n\t1.\tInspection Procedures \n\n\t\t(a)\tRemove rudder assembly from airplane. Remove rudder as outlined in the Ayres (Thrush) Maintenance Manual, Section VII. \n\n\t\t(b)\tStrip fabric and dope from area around upper hinge to facilitate the inspection as shown in Figure 1. \n\n\t\t(c)\tInspect with 10 power magnification in and around weld bead on upper hinge for cracks as shown in Figure 1. \n\n\t\t(d)\tIf no cracks are discovered, comply with paragraph 2. If no cracks are discovered, comply with paragraph 3\n\n\n\n\n\n\n\n\t2.\tAction required if cracks are discovered \n\n\t\tIf a crack or cracks are detected in the area of the upper hinge, accomplish any one of the available options listed below: \n\n\t\t(a)\tReplace the rudder assembly having the single upper hinge (P/N 54030-87) with the rudder assembly having triple upper hinges (P/N 54030-987) prior to further flight. \n\n\t\t(b)\tModify the single upper hinge rudder assembly in accordance with Ayres Custom Kit No. CK-AG-18 prior to further flight. \n\n\t(c)Replace the cracked single upper hinge rudder assembly with an airworthy single upper hinge rudder assembly prior to further flight and continue the paragraph 1. inspection at intervals not to exceed 100 hours' time in service. \n\n\t\t(d)\tRepair the single upper hinge rudder assembly in accordance with the procedures of Advisory Circular (AC) 43.13-1A, Chapter 2, prior to further flight and continue the paragraph 1. inspection at intervals not to exceed 100 hours' time in service. \n\n\t3.\tAction required if cracks are not discovered \n\n\t\tContinue the paragraph 1. inspection at intervals not to exceed 100 hours' time in service unless options (a) or (b) of paragraph 2. are accomplished. If accomplished, the repetitive inspections may then be discontinued. \n\n\tAyres Service Bulletin SB-AG-15 also pertains to this subject. \n\n\tCompliance with the provisions of this AD may be accomplished in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, SouthernRegion. \n\n\tThis amendment is effective May 23, 1979.
2014-25-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports from multiple operators that have found fatigue cracking in the corners of the forward galley service doorway. This AD requires repetitive inspections for any cracking of the skin and bear strap doublers in the corners of the forward galley service doorway, and corrective action if necessary. This AD also provides optional terminating actions for certain repetitive inspections. We are issuing this AD to detect and correct fatigue cracking, which could result in rapid loss of cabin pressure.