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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.