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80-18-10: 80-18-10 PIPER AIRCRAFT CORPORATION: Amendment 39-3903. Applies to all Models PA-23, PA-23-160, PA-23-235, PA-23-250, PA-E23-250, PA-31, PA-31-300, PA-31-325, PA-31-350, and PA-31P airplanes certificated in all categories. Compliance is required as indicated unless already accomplished. To prevent possible engine power loss due to malfunction of the fuel valves or fuel valve cable assemblies, accomplish the following: (a) On Models PA-23-235, PA-23-250, PA-E23-250, serial numbers 27-505 through 27-1999 and 27-2223 through 27-7305126; PA-31, PA-31-300 and PA-31-325, serial numbers 31-2 through 31-7300951; PA-31-350, serial numbers 31-5001 through 31-7305052; and PA-31P, serial numbers 31P-3 through 31P-7300147, equipped with Scott fuel selector valves, perform the following: NOTE: The requirements of paragraph (a) do not apply to those aircraft equipped with a Dukes valve. (1) Prior to the next flight, and at intervals not to exceed 10 hours time in service until compliance with paragraph (c), check both right and left fuel selector valves for smooth and easy operation before starting engines. If either fuel selector valve exhibits binding, sticking or is otherwise difficult to operate, accomplish paragraph (c) (1) or (c) (2), as applicable, before further flight. (b) On Models PA-23, PA-23-160; PA-23-235, PA-23-250, PA-E23-250, serial numbers 27-1 through 27-7954089; PA-31, PA-31-300, PA-31-325, serial numbers 31-2 through 31-7612065; and PA-31P, serial numbers 31P-1 through 31P-7730004, which have accumulated 300 or more hours in service, accomplish the following within 100 hours' time in service after the effective date of this AD unless already accomplished within the last 100 hours, and thereafter at intervals not to exceed 100 hours' time in service. (1) Visually inspect, using 10x power magnification, all fuel valve control cable wires at each swivel fitting and at idler control arm and actuating lever connections. Inspect for cracks, sharp radius bends and kinks in the control wires. Refer to Piper Service Bulletin No. 507 for inspection locations. Replace any cable inner wire that exhibits an adverse condition as described above with a like serviceable part. (2) In accordance with Piper Service Bulletin No. 507 and the appropriate Piper Service Manual, inspect all fuel valves and control cables through all detent positions by having someone operate the fuel controls in the cockpit while inspecting for the following: (i) Rigging and adjustment. (ii) Unrestricted motion of cable wires, swivel fitting and valve actuating levers. (iii) Proper lubrication of fuel valve attachments and controls. Correct any unsatisfactory conditions in accordance with the appropriate aforementioned Piper Service documents. (c) Within-the next 100 hours time in service after the effective date of this AD, unless already accomplished within the last 900 hours, and thereafter at intervals not to exceed 1,000 hours time in service, accomplish the following: NOTE: The requirements of paragraph (c) do not apply to aircraft equipped with a Dukes valve. (1) On Models PA-23-235, PA-23-250, PA-E23-250, serial numbers 27-505 through 27-1999 and 27-2223 through 27-7305126; PA-31, PA-31-300, and PA-31-325, serial numbers 31-2 through 31-7300951; and PA31P, serial numbers 31P-3 through 31P-73001 47, equipped with Scott fuel selector valves: (i) Gain access to the fuel selector valves in accordance with the appropriate Maintenance Manual. (ii) Visually inspect the cable wires at the fuel selector valve swivel fittings by having someone operate the fuel controls in the cockpit while inspecting the swivel fittings and control wires. (iii) If any evidence exists of the cable binding, bending, or kinking, replace the cable and carefully check the system rigging in accordance with the appropriate Maintenance Manual. (iv) Remove and disassemble the Scott fuel selector valves in accordance with the Maintenance Manual, under the section entitled "Fuel System." (v) Remove the existing valve spool "O" rings and install new ones contained in Piper Kit No. 760-504. (vi) Reassemble the fuel selector valves and inspect for leaks in accordance with the Maintenance Manual. (vii) Install the fuel selector valves in the aircraft and inspect for proper rigging and tank selection. Lubricate the external parts at the selector valve sprocket and control cable swivel fittings with an appropriate grease as specified in the Maintenance Manual. (viii) Inspect for fuel leaks from the fuel selector valves and fittings. (ix) Prepare the airplane for return to service in accordance with the Maintenance Manual. (x) Make an appropriate maintenance record entry. (2) For Model PA-31-350, serial numbers 31-5001 through 31-7305052, equipped with Scott fuel selector valves: (i) Remove the access plates located forward of the main spar on the underside of the wings, between the wing and the fuselage. (ii) Remove and disassemble the Scott fuel selector valves in accordance with the Maintenance Manual, under the section entitled "Fuel System." (iii) Remove the existing valve spool "O" rings and install new ones contained in Piper Kit No. 760-504. (iv) Reassemble the fuel selector valves and inspect for leaks in accordance with the Maintenance Manual. (v) Install the fuel selector valves in the aircraft and inspect for proper rigging and tank selection. (vi) Inspect for fuel leaks from the fuel selector valves and fittings. (vii) Install the access plates. (viii) Make an appropriate maintenance record entry. Upon submission of substantiating data, through an FAA Aviation Safety Inspector, the Chief, Engineering and Manufacturing Branch may adjust the inspection intervals. An equivalent method of compliance may be approved by the Chief,Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region or Eastern Region. The checks in paragraph (a) of this AD may be accomplished by the pilot as provided in FAR 43.3h and appropriate maintenance record entries made in accordance with FAR 91.173. Inspections and component replacements must be accomplished by a person authorized by FAR 43.3. NOTE: Piper Service Letter 580 and Service Bulletin Nos. 277, 507, and 648 pertain to this subject. This supersedes Amendment 39-3102, 43 FR 6411, AD 77-26-02. This amendment becomes effective September 8, 1980.
2006-12-10 R1: The FAA is revising an existing airworthiness directive (AD) that applies to certain Boeing Model 747-400 series airplanes. That AD currently requires inspecting the support bracket of the crew oxygen cylinder installation to determine the manufacturing date marked on the support, and performing corrective action if necessary. This new AD retains all the requirements of the existing AD and expands the applicability of the existing AD to include certain airplanes that are not on the U.S. Register. This AD results from a report indicating that certain oxygen cylinder supports may not have been properly heat- treated. We are issuing this AD to prevent failure of the oxygen cylinder support under the most critical flight load conditions, which could cause the oxygen cylinder to come loose and leak oxygen. Leakage of oxygen could result in oxygen being unavailable for the flightcrew or could result in a fire hazard in the vicinity of the leakage.
92-02-19 PL: 92-02-19 GARRETT ENGINE DIVISION, ALLIED-SIGNAL INCORPORATED: Priority Letter AD 92-02-19, issued on January 14, 1992. Applicability: Garrett Engine Division, Allied-Signal Incorporated Model TPE331-8, -10, -11, and -12 series turboprop engines installed on but not limited to Cessna Model 441 series (Conquest or Conquest II), Construcciones Aeronauticas, S.A. (CASA) 212 series, Twin Commander 695 series, Mitsubishi MU-2B series (Marquise/ Solitaire), Fairchild SA226 and SA227 series (Merlin and Metro), and British Aerospace (BAe) Jetstream 3101 and 3201 series (31 and 32) aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent an engine fire caused by a fuel manifold assembly leak, accomplish the following: (a) Within the next 50 hours time in service after receipt of this Priority Letter AD, remove from service in accordance with the Accomplishment Instructions of Garrett Engine Division, Allied-Signal Alert Service Bulletin (SB) No. TPE331-A73-0198, Revision 1, dated January 10, 1992, Stratoflex fuel manifold assemblies, Part Number 3102469-2, manufactured on the dates listed in the SB, and those fuel manifold assemblies having no identification tag. (b) Prior to further flight replace affected fuel manifold assembly with a serviceable part. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the Priority Letter AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), an alternative method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, Aircraft Certification Service, FAA, 3229 East Spring Street, Long Beach, California 90806-2425, may approve an equivalent means ofcompliance or adjustment of the compliance schedule which provides an equivalent level of safety. This Priority Letter AD 92-02-19, issued on January 14, 1992, becomes effective immediately upon receipt.
77-13-20: 77-13-20 ROLLS ROYCE (1971), LTD: Amendment 39-2945. Applies to Bristol Viper MK. 522 and MK. 601-22 engines installed, or being held for installation, on Hawker Siddeley Model DH/BH-125 series airplanes, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent interference between the engine throttle control rod and the high pressure fuel shutoff valve that could result in inability to actuate fuel shutoff, accomplish the following: (a) For installed engines, within the next 500 hours engine time in service after the effective date of this AD, accomplish the following in accordance with paragraph 2.A of Rolls Royce Alert Service Bulletin 73-A98 (MK. 522 engines) or 73-A13 (MK. 601-22 engines), both dated October 1975, or an FAA-approved equivalent: (1) Relocate the ident/data tags fitted to the fuel tube, P/N DF-21-389. (2) Check for adequate clearance between the fuel tube, P/N DF-21-389, and the H.P.cock control rod, P/N 25CX53-25A. (3) If the clearance is found not to be adequate during the inspection specified in paragraph (a)(2) of this paragraph, realign the fuel tube to provide adequate clearance. (b) For other engines, prior to installation on a Model DH/BH-125 airplane, ascertain the location of the ident/data tags on fuel tube P/N DF-21-389 and if it is found to be within 8 inches or less of the union nut, at the b.f.c.u. connection, remove the tags and refit to a lower position on the tube in accordance with the instructions contained in paragraph 2.B of Rolls Royce Alert Service Bulletin 73-A98 (MK. 522 engines) or 73-A13 (MK. 601-22 engines), both dated October 1975, or an FAA-approved equivalent. NOTE: The accomplishment instructions contained in Rolls Royce Alert Service Bulletins 73-A13 and 73- A98 are identical. This amendment becomes effective on August 1, 1977.
2020-06-15: The FAA is adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. This AD was prompted by a report of a crack found in the inboard boom of the left- hand frame at fuselage station (STA) 17011. This AD requires a detailed inspection of the fuselage at STA 17011 for any cracking, repair if necessary, and a reporting requirement, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
80-15-13: 80-15-13 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 3856. Applies to Model AS 350 series helicopters, certificated in all categories, which have main rotor assembly, P/N 350A.37.0003, serial numbers M1 through M146 installed. Compliance required as indicated. To rectify incorrect installation of the rotating star drive adapter which could result in vibration and premature wear of the rotating star bolts, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished: (1) Measure the dimension between the spacer and the upper face of the rotating drive adapter, P/N 350A.36.1119, at locations no more than 120 degrees apart using a fixed length block and a feeler gage. (2) Compare the measurements. (b) If the measurement comparison required in paragraph (a)(2) of this AD reveals a variation of 0.039 inches (1 mm) or less, return to service and comply with paragraph(d) of this AD. (c) If the comparison required in paragraph (a)(2) of this AD reveals a variation in excess of 0.039 inches (1 mm), reposition the rotating star drive adapter perpendicular to the drive shaft in accordance with sub-paragraph 2. of paragraph C, "DESCRIPTION," of Aerospatiale (SNIAS) Service Bulletin No. 65.01, dated October 20, 1978, or an FAA-approved equivalent. NOTE: The AS 350 Maintenance Manual Work Card No. 65.13.603 pertains to this same subject. (d) Following any maintenance action on the rotating star drive adapter bolt, comply with paragraph (a)(1), (a)(2), and paragraph (b) or (c) of this AD. (e) For a rotor assembly with a serial number M1 through M146, held as spare, comply with this AD at installation and release to service. (f) For purposes of this AD, an FAA-approved equivalent may 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 August 7, 1980.
76-20-02: 76-20-02 PRATT & WHITNEY AIRCRAFT: Amendment 39-2734. Applies to all Pratt & Whitney Aircraft JT8D-1, -1A, -1B, -7, -7A, and -7B engines. Compliance required prior to June 30, 1978, unless already accomplished. To preclude liberation of second stage fan blades: A. Inspect the blade retaining strap for taper wear in accordance with Section 72-33-1 of Pratt & Whitney Aircraft JT8D Series Engine Manual P/N 481672, Revision 78, or later FAA approved revision or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. Remove from service, second stage fan blades with taper wear in excess of .0025 inch before further flight. B. Install second stage fan blade bumper, P/N 642409, in accordance with Pratt & Whitney Aircraft Service Bulletin 2406 or later FAA approved revision or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance date 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 that operator. The manufacturer's service bulletins 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 Pratt & Whitney Aircraft, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. Ahistorical file on this AD which includes the incorporated material in full is maintained by the Federal Aviation Administration at its headquarters in Washington, D.C., and at the New England Regional Office in Burlington, Massachusetts. This amendment becomes effective on October 10, 1976.
98-25-53: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) T98-25-53 that was sent to all known U.S. owners and operators of all Airbus Model A300 B4-600R and A300 F4-600R series airplanes by individual telegrams. This AD requires a one-time visual inspection for damage of the center fuel pumps and fuel pump canisters, and replacement of damaged fuel pumps and fuel pump canisters with new or serviceable parts. This action is prompted by reports of damaged center tank fuel pump canisters and damaged center tank fuel pumps. The actions specified by this AD are intended to detect damage to the fuel pump and fuel pump canister, which could result in loss of flame trap capability and could provide a fuel ignition source in the center fuel tank.
73-07-04: 73-07-04 BENDIX ELECTRICAL COMPONENTS DIVISION: Amdt. 39-1611 as amended by Amendment 39-1731. Applies to all Bendix Electrical Components Division of the Bendix Corp. (Bendix Scintilla) S4LN or S4RN, S6LN or S6RN and S8LN or S8RN magnetos with series numbers -20 through -26, -200 through -206, -600 through -604 and -1200 through -1227 except the following. 1. Magnetos identified with the Bendix Blue name plate (Bendix remanufactured magnetos) having serial No. 231001 or higher. 2. Magnetos identified with the Bendix Red name plate (new magnetos) having a serial number with the prefix "A" and No. 16058 or higher. Compliance required as indicated after the effective date of this AD unless previously accomplished. To prevent failure of these magnetos due to malfunction or failure of the ignition coil or rotating magnet, accomplish the following: a. On magnetos having 1,800 or less hours in service since new or last overhaul on the effective date of this AD, accomplish paragraph "d" before accumulation of 2,000 hours in service. b. On magnetos having more than 1,800 hours in service since new or last overhaul, accomplish paragraph "d" within the next 200 hours service after the effective date of this AD. c. Magnetos whose time in service since new or last overhaul is unknown will be assumed to have a total of 1,800 hours minimum and thus fall within the requirements of paragraph (b). d. Identify magnetos per instructions contained in Bendix Electrical Components Division Service Bulletin No. 560, dated August 1972 or later. Magnetos having ignition coils as described in paragraph A, or rotating magnets as described in paragraph B or shown in figure 2 of Bendix Electrical Components Division's Service Bulletin No. 560, dated August 1972 or later, must have these components removed and replaced with serviceable parts as listed in the applicable Bendix Electrical Components Division Service Parts List, numbered and dated as follows or subsequent: Magneto Model Parts List Designation Parts List Date S4LN-20 series (ignition coil no. 10-160886 or subsequent). L-227-9 December 1963 S6LN-20 series (ignition coil no. 10-160886 or subsequent). L-223-11 October 1963 S-200 series (ignition coil no. 10-160887 or subsequent). L-528-3 October 1963 S-600 series (magnet rotor only) L-552-3 December 1964 S-1200 series (ignition coil only) L-608-3 September 1971 e. Upon completion of paragraph d, identify each magneto as follows: S-20, S-200, and S-600 series magnetos - Metal stamp .010 deep maximum the letter "A" 3/16 inches high, midway and centered between the timing plug boss and the curved surface at the rear of distributor housing. S-1200 series magnetos - Metal stamp .010 deep maximum the letter "A" 3/16 inches high, centered between the timing plug boss and data plate, adjacent to the magneto housing rib. Amendment 39-1611 became effective April 2, 1973. This amendment 39-1731 becomes effective October 11, 1973.
80-14-02: 80-14-02 PIPER AIRCRAFT CORPORATION: Amendment 39-3819. Applies to Model PA-28-181, serial numbers 28-7790032 through 28-8090227; Model PA-32-300, serial numbers 32-7640001 through 32-7740032 and Model PA-32R-300, serial numbers 32R-7680001 through 32R-7780148 airplanes certificated in all categories. Compliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent separation of the throttle control cable rod end from the throttle arm on the affected Models PA-28 and PA-32 airplanes, and rod end binding with possible subsequent throttle cable failure on the affected Model PA-28 airplanes, accomplished the following. (a) For the Model PA-32-300 and PA-32R-300 series airplanes, replace the throttle linkage connecting hardware in accordance with the instructions contained in Piper Service Bulletin No. 537, dated January 12, 1977. (b) For the Model PA-28-181 airplanes, modify the throttle linkage in accordance with the instructions listed in the "Throttle Linkage Modification Kit," Piper Part Number 764- 009V. NOTE: Piper Service Bulletin No. 679 pertains to this subject. (c) Make an appropriate maintenance record entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. This amendment is effective July 10, 1980.