Results
2017-26-10: We are superseding Airworthiness Directive (AD) 2015-08-01, which applied to certain The Boeing Company Model 757 airplanes. AD 2015-08-01 required, depending on \n\n((Page 61676)) \n\nairplane configuration, installing new relays and bracket assemblies, inspecting to ensure that the new relays do not contact adjacent wire bundles, torqueing the bracket assembly installation nuts and ground stud nuts, retesting the bond resistance between the bracket assemblies and the terminal lugs on the ground studs, and doing related investigative and corrective actions if necessary. This AD does not retain any requirements, and instead requires deactivating the spoiler control module relays and capping and stowing the associated wiring on airplanes on which the actions required by AD 2015-08-01 have been done. This AD was prompted by a report of an uncommanded spoiler movement during flap configuration just before landing, on an airplane on which the actions required by AD 2015-08-01 hadbeen done. We are issuing this AD to address the unsafe condition on these products.
88-19-08: 88-19-08 BRITISH AEROSPACE: Amendment 39-6010. Applies to Model BAC 1-11 series airplanes equipped with R.F.D. AES-12B inflatable escape slides, identified in British Aerospace BAC 1-11 Service Bulletin 25-PM5943, Revision 1, dated May 8, 1987, certificated in any category. Compliance is required within 5 months after the effective date of this AD, unless previously accomplished. To prevent failure of the emergency escape slide deployment system, accomplish the following, unless previously accomplished: A. Modify the R.F.D. Type AES-12B emergency escape slide system in accordance with BAC 1-11 Service Bulletin 25-PM5943, Revision 1, dated May 8, 1987. 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 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. 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, 39-6010, becomes effective October 10, 1988.
61-20-02: 61-20-02 PIPER: Amdt. 336 Part 507 Federal Register September 20, 1961. Applies to Model PA-24 "250" Aircraft Serial Numbers 24-103 to 24-1629 Inclusive, Which Do Not Have a Reinforcing Plate Welded to the Stack in the Area Where the Rear Engine Cylinder Stack is Welded to the Exhaust Stack Assembly. Compliance required as indicated. Due to incidents of cracks occurring in the exhaust stack assembly, right side, P/N 21664-03, the following inspections and reinforcement must be accomplished: (a) Within 25 hours' time in service after effective date of this AD, remove the carburetor heat shroud assembly, P/N 21664-03, for any indication of cracks or deterioration particularly in the area where the rear engine cylinder exhaust stack is welded to the exhaust stack assembly. If evidence of cracks or deterioration is noted, the assembly must be replaced with a new assembly prior to further flight. The provisions of this paragraph shall be reaccomplished at intervals of50 hours' time in service until such time as the installation in paragraph (b) is accomplished. (b) Within 100 hours' time in service after initial compliance with paragraph (a), a clamp-on reinforcement Piper Kit No. 754396 or equivalent, shall be installed on the exhaust stack assembly, P/N 21664-03. After installation of the clamp-on reinforcement, the provisions of paragraph (a) are no longer applicable. (Piper Service Bulletin 202 dated May 22, 1961, applies to this subject.) This directive effective October 20, 1961.
61-16-01: 61-16-01 AERONCA: Amdt. 320 Part 507 Federal Register August 8, 1961. Applies to All Model 15 Series Aircraft. Compliance required as indicated. As a result of cracks found on the wing lift strut fittings, P/N 5-463-2, the following inspection shall be accomplished. For those aircraft with 1,000 or more hours' time in service, the inspection shall be accomplished within 25 hours' time in service after the effective date of this AD, unless accomplished within the last 25 hours' time in service, and at each periodic inspection thereafter. For those aircraft with less than 1,000 hours' time in service, the inspection shall be accomplished at the next periodic inspection after the effective date of this AD, and at each periodic inspection thereafter. (a) Detach the wing lift strut assembly and remove the upper and lower 1 1/2-inch diameter, 2024 tubular fittings, P/N 5-463-2. Clean, remove the paint and polish lightly with crocus cloth so as to increase the contrastfor inspection. Using the dye penetrant method and a 10-power glass, or equivalent, inspect for cracks on the inside and outside of the fitting surfaces, particularly in the area of the bolt holes and 90 degrees to the centerline of the bolt holes. All cracked tubes and all tubes with an outside diameter exceeding 1.515 inches at any point must be replaced prior to further flight. (b) Fittings being reinstalled shall be finished with the following or equivalent: Two coats of zinc chromate primer on the inside and outside of the fitting and finish enamel on the outside of the fitting. The 1/4-inch bolts attaching the fitting to the strut and the 1/2-inch bolt attaching the strut assembly to the airplane shall be torqued only enough to bring the respective parts into contact. The fitting must not be forced out of round. (c) When it is necessary to install new fittings, Aeronca P/N 5-463-2, Champion Aircraft Corporation P/N 1-9280, Prentice Aircraft, Inc. P/N 61-16-1, orFAA approved equivalent may be used. Existing AN 4 bolts, if not damaged, may be reinstalled in holes that match. No elongation of old holes in struts is permissible. (d) The following rework may be used if the holes in new fittings and old struts do not match to allow proper installation. AN5 bolts may be installed in all holes or in any combination. (1) If holes do not match, line-drill the assembled strut and fitting (19/64 inch) and ream to accept an AN 5 bolt. (.3125 inch minimum, .3135 inch maximum diameter.) In the event that portable equipment must be used, drill the hole 19/64 inch and accomplish the final sizing with a tapered hand reamer to assure alignment. (2) Install AN 5-22A bolts each with two AN 960-516 washers, and AN 365-524 nuts in holes that require rework. (e) When Prentice Aircraft, Inc., P/N 61-16-1 or FAA approved equivalent is installed, the repetitive inspections required by this directive may be discontinued. (Aeronca Service Helps and Hints No. 59 and Champion Aircraft Corporation Service Helps and Hints No. 59 cover the same subject.) This directive effective August 18, 1961. Revised November 28, 1961. Revised April 10, 1962.
61-16-07: 61-16-07 SUD AVIATION: Amdt. 321 Part 507 Federal Register August 5, 1961. Applies to All Alouette II SE 3130 Helicopters. Compliance required as indicated. As a result of two cases of cracks in the main rotor hubs, all main rotor hubs P/N 3130. S12.20.001 must be retired from service upon accumulation of 660 hours' time in service, except that main rotor hubs which have already accumulated 650 or more hours' time in service on the effective date of this directive must be retired from service within the next 10 hours' time in service. (Sud Aviation Helicopters Service Alouette II SE 3130 No. AL 12.11.204 covers this subject.) This directive effective August 5, 1961.
2017-26-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200 series airplanes. This AD was prompted by a report indicating that the main cargo door (MCD) forward-most cam latch on the forward center cam latch pair broke during flight. This AD requires repetitive inspections for discrepancies of cam latches, latch pins, and latch pin cross bolts of the MCD; replacement of all alloy steel latch pin cross bolts with corrosion-resistant steel (CRES) latch pin cross bolts of the MCD; and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2005-09-05: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC120 helicopters that requires inspecting the tail rotor drive shaft (drive shaft) damper half-clamps (half-clamps) to determine if they are centered on the friction ring, and if not correctly positioned, centering the half-clamps on the friction ring. This amendment is prompted by the discovery of half- clamps that were incorrectly positioned. The actions specified by this AD are intended to detect incorrect positioning of the drive shaft half-clamps, and to prevent interference of the half-clamps with the drive shaft, which could result in scoring on the drive shaft, failure of the drive shaft, and subsequent loss of control of the helicopter.
85-25-06: 85-25-06 McDONNELL DOUGLAS: Amendment 39-5177. Applies to McDonnell Douglas Model DC-9 and C-9 (Military) series airplanes, fuselage numbers 1 through 1165, certificated in any category. Compliance required as indicated unless previously accomplished. \n\n\tTo eliminate a potential fire ignition source from the generator power feeder cable installation, accomplish the following: \n\n\tA.\tWithin 12 months after the effective date of this airworthiness directive (AD), for all McDonnell Douglas DC-9 and C-9 (Military) series airplanes, inspect and repair, as necessary, power feeder cable installation in accordance with the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 24-78, dated April 9, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tWithin 12 months after the effective date of this airworthiness directive (AD), modify the power feeder cable installation on all McDonnell Douglas Model DC-9-81 and DC-9-82 series airplanes in accordance with the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 24-78, dated April 9, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tAlternate 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. \n\n\tD.\tSpecial 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. \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 theFAA, 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 January 10, 1986.
61-16-06: 61-16-06 PIPER: Amdt. 314 Part 507 Federal Register July 29, 1961. Applies to All PA- 24 and PA-24 "250" Aircraft Modified to Incorporate Brittain Wing Tip Fuel Tanks (Supplemental Type Certificates Nos. SA4-1235 and SA4-1351). Compliance required within the next 150 hours' time in service after the effective date or at the next disassembly of fuel selector valves, whichever occurs first. The fuel selector valve handles of aircraft equipped with Brittain wing tip fuel tanks can easily be reinstalled with incorrect indexing after the valves have been disassembled for servicing and lubrication. Incorrect indexing can cause serious fuel system malfunctioning and one accident resulting from this condition has been reported. To preclude future incorrect indexing of the fuel selector valve handles, the following must be accomplished: (a) Remove any valve shafts with four flat sides at the handle end and replace with Brittain P/N 4018-15 shafts, or equivalent. The Brittain P/N 4018-15 shaft is identical to the original except that one of the four sides at the handle end has been modified to a convex shape. (b) After reassembly and reinstallation of the selector valves, determine that the valve handles are properly indexed with respect to the selector valve placard. (Brittain Aircraft Enterprises Service Letter No. 4000-1 dated April 26, 1961, covers this same subject.) This directive effective August 31, 1961.
2017-25-17: We are superseding airworthiness directive (AD) 2011-27-08 for Agusta S.p.A. (Agusta) Model A109S and AW109SP helicopters. AD 2011-27- 08 required repetitively inspecting each elevator assembly for a crack. This new AD retains the initial inspection interval and adds a repetitive borescope inspection. This AD is prompted by the discovery of another crack on an elevator assembly since AD 2011-27-08 was issued. The actions of this AD are intended to prevent an unsafe condition on these helicopters.
2017-25-12: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracking in the webs of the stub beams at certain fuselage stations. These cracks are the result of fatigue caused by cyclical loading from pressurization, wing loads, and landing loads. This AD requires repetitive inspections for cracking of the webs of the stub beams at certain fuselage stations, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2005-07-21: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747-200F and -200C series airplanes, that currently requires repetitive detailed inspections or a one-time open-hole high frequency eddy current inspection to detect cracking of certain areas of the upper deck floor beams, and corrective actions if necessary. This amendment requires new one-time inspections for cracking of the web, upper chord, and strap of the upper deck floor beams. This action also requires modifying or repairing the upper deck floor beams, as applicable, which eventually necessitates accomplishment of new repetitive inspections for cracking of the upper deck floor beams. The actions specified by this AD are intended to prevent fatigue cracks in the upper chord and web of upper deck floor beams and the resultant failure of such floor beams. Failure of a floor beam could result in damage to critical flight control cables and wire bundles that pass through the floor beam, and consequent loss of controllability of the airplane. Failure of the floor beam also could result in the failure of the adjacent fuselage frames and skin, and consequent rapid decompression of the airplane. This action is intended to address the identified unsafe condition. \n\nDATES: Effective May 16, 2005. \n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 16, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 747-53A2420, dated March 26, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as of May 11, 1998 (63 FR 20311, April 24, 1998).
2005-08-06: The FAA adopts a new airworthiness directive (AD) for all CENTRAIR 101 series gliders with other than elevator or aileron part number (P/N) SY991A hinge pins installed. This AD requires you to replace any installed elevator or aileron hinge pins that are not P/N SY991A hinge pins with P/N SY991A pins. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. We are issuing this AD to replace incorrectly heat-treated elevator or aileron hinge pins, which could result in failure of the elevator or ailerons. Such failure during takeoff, landing, or flight operations could lead to loss of glider control.
2017-25-14: We are adopting a new airworthiness directive (AD) for Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by a report of an engine multiple fan blade-off (MFBO) event, caused by engine fan flutter. We are issuing this AD to address the unsafe condition on these products.
61-14-06: 61-14-06 SNOW: Amdt. 306 Part 507 Federal Register July 11, 1961. Applies to All Model S2A Aircraft (Restricted Category). Initial compliance required within 25 hours' time in service after the effective date of this AD unless accomplished within 75 hours' time in service preceding such date. Subsequent compliance required at each 100 hours' time in service after the initial compliance date. Due to reports of excessive cable wear occurring at two AN 210-3B pulleys in the aileron system aft of the hopper and two AN 210-3B pulleys in the elevator system on the left and right of the pilot seat, the following must be accomplished: (a) Detach the aileron and elevator cables by disconnecting the turnbuckles to obtain slack at the two pulleys in each system. Visually inspect the cables for fraying by flexing the cable in the areas of pulley contact in accordance with Snow Service Letter No. 4. Replace all frayed cables prior to further flight. (b) Inspection of theelevator cable may be discontinued when the two AN 210-3B elevator system pulleys to the left and right of the pilot seat are replaced with AN 210-4B pulleys, in accordance with Snow Service Letter No. 6. Inspection of the aileron cable may be discontinued when the aileron cable system is replaced with a push-pull tube system in accordance with Snow Service Letter No. 7. (Snow Service Letters 4, 6, and 7 cover this subject.) This directive effective July 21, 1961.
61-14-01: 61-14-01 AERO COMMANDER: Amdt. 303 Part 507 Federal Register July 7, 1961. Applies to All Model 500 Aircraft. Compliance required within the next 100 hours' time in service after the effective date of this directive and at each 100 hours' time in service thereafter. Visually inspect the inside of angles P/N 5620023-7, -8, -9, and -10 in the area of the row of Huck bolts, nearest the radius of the angle, that attach the angles to the upper and lower mount fittings, P/N 3620025-1 and -2. If cracks are found, prior to further flight, incorporate the reinforcement as indicated in Aero Commander Service Bulletin No. 68A, dated January 20, 1961, or equivalent. Angles incorporating Federal Aviation Agency approved reinforcement need not be reinspected in accordance with the provisions of this AD. (Aero Commander Service Bulletin No. 68A dated January 20, 1961, covers this subject.) This supersedes AD 60-26-01. This directive effective August 8, 1961.
89-06-01: 89-06-01 SWITLIK PARACHUTE COMPANY, INC.: Amendment 39-6075. Applicability: Switlik TSO-C13 Life Preservers and TSO-C72 Individual Flotation Devices: all models and all part numbers manufactured from September 1, 1984, through January 30, 1985, and June 1, 1985, through October 30, 1985 (date located on identification label on front surface). Compliance: Required within one year after the effective date of this AD, unless already accomplished. To prevent the improper functioning of the carbon dioxide (CO2) inflators on TSO-C13 Life Preservers and TSO-C72 Individual Flotation Devices, accomplish the following: (a) Visually inspect the CO2 inflators for cracks and chipping and, if necessary, replace CO2 inflators with serviceable parts in accordance with Paragraph 2, Accomplishment Instructions of Switlik Parachute Company, Inc., Service Bulletin No. 25-00-19, dated September 8, 1987. (b) 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. (c) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, Federal Aviation Administration, Engine and Propeller Directorate, Aircraft Certification Service, 181 South Franklin Avenue, Valley Stream, New York 11581. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, New York Aircraft Certification Office, Federal Aviation Administration, Engine and Propeller Directorate, Aircraft Certification Service, 181 South Franklin Avenue, Valley Stream, New York 11581, may adjust the compliance time specified in this AD. Switlik Service Bulletin No. 25-00-19, dated September 8, 1987, 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 already received this document from the manufacturer may obtain copies upon request to Switlik Parachute Co., Inc., 1325 East State Street, P.O. Box 1328, Trenton, New Jersey 08607. This document may also be examined at the Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket No. 88-ANE-05. This amendment (39-6075, AD 89-06-01) becomes effective on April 3, 1989.
88-21-06: 88-21-06 ROLLS-ROYCE plc: Amendment 39-6031. Applies to Rolls-Royce plc (R-R) (Formerly Rolls- Royce Limited) Dart Mks. 506, 510, 511, 514, 525, 526, 527, 528, 529, 531, 532, and 542 series turboprop engines and all variants. Compliance is required as indicated, unless already accomplished. To prevent low cycle fatigue failure of high pressure (HP) impellers and low pressure (LP) impellers, accomplish the following: (a) Remove from service HP impellers installed in Dart Mks. 506, 510, 511, 514, and all variants, in accordance with the following schedule: (1) HP impellers to Mod 844 standard which have accumulated 8,000 or more total flights since new on the effective date of this AD, within the next 400 flights from the effective date of this AD, or within the next 12 calendar months from the effective date of this AD, whichever comes later. (2) HP impellers to Mod 1455 standard which have accumulated 8,600 or more total flights since new on the effective date of this AD, within the next 400 flights from the effective date of this AD, or within the next 12 calendar months from the effective date of this AD, whichever comes later. (3) HP impellers to Mod 844 standard which have accumulated less than 8,000 total flights since new on the effective date of this AD, at or prior to accumulating 8,400 total flights since new, or within 12 calendar months from the effective date of this AD, whichever comes later. (4) HP impellers to Mod 1455 standard which have accumulated less than 8,600 total flights since new on the effective date of this AD, at or prior to accumulating 9,000 total flights since new, or within 12 calendar months from the effective date of this AD, whichever comes later. NOTES: (1) Total flights since new is defined as the total number of flights accumulated by the part since first installation in an engine. This total includes all Mod standards the part has operated under. (2) This action establishes a new Overhaul Manual Chapter 5 life limit for HP impellers, as noted in items (a)(3) and (a)(4) above. (3) Reference R-R Service Bulletin (SB) DA72-496, dated June 1986. (b) Remove from service HP impellers installed in Dart Mks. 525, 526, 527, 528, 529, 531, 532, 542, and all variants, on or before the life limits in the following schedule: Life Limit in Number of Flights Dart Mk. Pre-Mod 797 Mod 797 Open Bore Processed Mod 797 Pre-Mod 1455 Mod 1455 Mod 1475 525 thru 529 4,500 11,000 14,000 NC NC 531 and 532 4,500 11,000 14,000 NC NC 542 NA NA 12,000 16,000 14,500 (Since incorp. of Mod 1455) NA - Model not applicable to specific impeller. NC - Life limits not covered by this AD. Information relating to these impellers is contained in the manufacturer's appropriate overhaul manual. NOTE: The above noted HP impeller life limits were published in AD 73-21-04, Amendment 39-1734 (38 FR 27819), and have notchanged. This section is only intended to reprint for clarity, already existing AD requirements with respect to current R-R SB information. (c) Remove from service LP impellers installed in Dart Mks. 506, 510, 511, 514, 525, 526, 527, 528, 529, 531, 532, 542, and all variants, on or before the life limits in the following schedule: Limit in Number of Flights Dart Mk. Mod 797 Open Bore Processed Mod 797 Pre-Mod 1455 Mod 1455 506 10,500 11,250 11,250 510 10,500 11,250 11,250 511 10,500 11,250 11,250 514 10,500 11,250 11,250 525 thru 529 9,000 9,000 9,000 531 and 532 9,000 9,000 9,000 542 NA 9,000 9,000 NA - Model not applicable to specific impeller. NOTES: (1) LP impellers to Mod 1455 Part 1 standard (manufactured by R-R to this standard) are not affected by this AD. Life limits for this part are quoted in the overhaul manual, Chapter 5, "Time Limits". (2) The above noted LP impeller life limits were published in AD 73-21-04, Amendment 39-1734 (38 FR 27819), and have not changed. This AD, with respect to LP impeller life limits, is only intended to reprint for clarity, already existing AD requirements with respect to current R-R SB information. (3) Rolls-Royce Dart SB 72-463 also pertains to LP impeller life limits. (d) Aircraft may be ferried in accordance with provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. (f) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, may adjust the compliance schedules specified in this AD. This amendment supersedes Amendment 39-1734 (38 FR 27819), AD 73-21-04. This amendment, 39-6031, becomes effective on November 6, 1988.
2017-25-02: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 1000, 2000, 3000, and 4000 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by reports indicating that certain exit signs have a hydrogen isotope that decays over time, causing the signs to lose their brightness. We are issuing this AD to address the unsafe condition on these products.
89-09-04: 89-09-04 SAAB-SCANIA: Amendment 39-6194. Applicability: Model SF-340A series airplanes, serial numbers -003 through -138, inclusive, certificated in any category. Compliance: Required as indicated below, unless previously accomplished. To prevent reduced structural capability of the fuselage, accomplish the following: A. Within 30 days after the effective date of this AD, perform an inspection of the insulation in the Environmental Control System (ECS) compartment and secure the Gamah Couplings with a locking wire, in accordance with SAAB-Scania Service Bulletin SF340-21-022, dated October 31, 1988. B. If the inspection required by paragraph A., above, reveals leakage of hot air, prior to further flight, inspect for delamination of the stringer to skin bonding, and repair, if necessary, in accordance with SAAB-Scania Service Bulletin SF340-53-025, dated October 31, 1988. 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 Manger, 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. D. 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. 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 AB, S-581 88, 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 (39-6194, AD 89-09-04) becomes effective on May 16, 1989.
87-06-04: 87-06-04 AEROSPATIALE: Amendment 39-5569. Applies to Model ATR-42 series airplanes listed in Aerospatiale Service Bulletin ATR 42-25-0006, dated July 21, 1986, fitted with IPECO flight crew seats, certificated in any category. Compliance is required within 30 days after the effective date of this AD, unless already accomplished. To prevent collapse of the pilot or co-pilot seat backs, accomplish the following: A. Modify seats, P/N 3A063-0035, 3A063-0036, 3A063-0079, and 3A063-0080, in accordance with Aerospatiale Service Bulletin ATR 42-25-0006, dated July 21, 1986, or Revision 1, dated September 3, 1986 (Reference IPECO Service Bulletin A001-25-22, dated June 5, 1986). 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. C. 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 the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective April 2, 1987.
88-07-52: 88-07-52 AEROSPATIALE: Amendment 39-5925. Applies to Model ATR-42-200 and -300 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent erroneous fuel quantity readings in the fuel indication system, accomplish the following: A. Within 7 days after the effective date of this AD, modify the cable in the fuel indicator panel, as follows: 1. Remove fuel quantity indicator 3 quart on the 4 VU panel (Ref: Airplane Maintenance Manual (AMM) 28-42-81-RAI 10000). 2. Disconnect cable 2842-0007 from plug 3 Qta pin R. 3. Insulate the cable from circuitry by means of heat shrinkable sleeve. 4. Attach cable to harness by suitable tie wrap. 5. Reinstall 3 Qta plug and 3 quart indicator (Ref: AMM 28-42-81-RAI 10000). 6. Perform a test of the fuel quantity indicator by pushing the test switch. Ensure that all digits indicate "eight," and that the "low level" lights illuminate. B.Accomplishment of the modification of the cable in the fuel indicator panel and functional test in accordance with Aerospatiale Service Bulletin ATR42-28-0011, dated April 6, 1988, is considered an acceptable means of compliance with 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. 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, 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 for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This AD was effective earlier to all recipients of telegraphic AD T88-07-52, issued March 31, 1988. This Amendment 39-5925 becomes effective June 4, 1988.
61-12-02: 61-12-02 DOUGLAS: Amdt. 294 Part 507 Federal Register June 7, 1961. Applies to All Model DC-8 Aircraft powered with P&WA JT3C-6 and JT4A Series Engines. \n\n\tCompliance required as indicated. \n\n\tAn instance has been reported wherein a takeoff was attempted with elevator gust lock engaged. It was found that the throttle interlock did not provide adequate restriction to limit engine thrust under the prevailing temperature condition. Unless already accomplished, the following modification or FAA approved equivalent, must be accomplished within the next 500 hours' time in service. \n\n\tModify the throttle interlock system to provide further restriction of the throttles when elevator gust lock is engaged by installing the following parts or equivalent: \n\n\tPushrod - Gust Lock Interlock Pedestal, P/N 3771190. \n\n\tAdapter - Gust Lock Crank, P/N 4771191. \n\n\tArm, Gust Lock Interlock Pedestal, P/N 2772271-1 or -501. \n\n\tPer Douglas Drawing No. 5640901 Changes "CI" and "CK" - "Pedestal Assembly - Accessory Controls". \n\n\t(Douglas Service Bulletin No. A27-99, reissue No. 1, revision No. 2 dated July 19, 1961, also covers this same subject.) \n\n\tThis directive effective June 7, 1961. \n\n\tRevised August 26, 1961.
87-08-04: 87-08-04 BOEING: Amendment 39-5593. Applies to Model 757 series airplanes equipped with Rolls Royce RB211-535E4 engines, as listed in Boeing Service Bulletin 757-78-0010, dated December 23, 1986, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo maintain the fire integrity of the thrust reverser C-ducts, accomplish the following within the next 250 flight hours after the effective date of this AD: \n\n\tA.\tInspect and repair, if necessary, the thermal blanket in the upper 45 degree section of the C-ducts, as described in Boeing Service Bulletin 757-78-0010, dated December 23, 1986, or later FAA-approved revision. Any damage to the thermal blanket (such as holes, splits, and tears) must be repaired prior to further flight. \n\n\tB.\tInspect and repair, if necessary, the thermal blanket in the lower section of the C- ducts and engine components, as described in the Boeing Service Bulletin 757-78-0010, dated December 23, 1986, or later FAA-approved revisions. Any damage discovered must be repaired within the next 250 flight hours. \n\n\tC.\tAn 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, 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 repair required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124-2207. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective April 16, 1987.
2017-24-07: We are superseding Airworthiness Directive (AD) 2014-08-01, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014-08-01 required an inspection for part numbers of the interconnecting struts and, for affected interconnecting struts, identification of the part and serial numbers of the associated target and proximity sensors and replacement or re-identification of the flap interconnecting strut if necessary. This AD continues to require an inspection to verify the interconnecting strut part number. This AD also provides a new compliance time and an additional inspection for previously inspected airplanes. This AD was prompted by an investigation that showed that when a certain combination of target/ proximity sensor serial numbers is installed on a flap interconnecting strut, a ``target FAR'' signal cannot be detected when reaching the mechanical end stop of the interconnecting strut. We are issuing this AD to address the unsafe condition on these products.