Results
2016-15-01: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of partial loss of no-back brake (NBB) efficiency on the trimmable horizontal stabilizer actuator (THSA). This AD requires an inspection to determine THSA part numbers, serial numbers, and flight cycles on certain THSAs; and repetitive replacement of certain THSAs. We are issuing this AD to prevent loss of THSA NBB efficiency, which, in conjunction with the inability of the power gear to keep the ball screw in its last commanded position, could lead to an uncommanded movement of the horizontal stabilizer, possibly resulting in loss of control of the airplane.
70-06-05: 70-06-05 BRITTEN-NORMAN, LTD: Amdt. 39-956. Applies to BN-2 and BN-2A airplanes. To prevent failure of the elevator trim system final drive lever attachment lugs, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 25 hours' time in service since the last inspection until the modifications of paragraph (b) have been accomplished, visually inspect the elevator trim system final drive lever (P/N NB-45-D-1823) for cracks in accordance with Britten-Norman Service Bulletin No. BN-2/SB.24 dated January 8, 1969, or later ARB-approved issue or an FAA-approved equivalent. (b) If cracks are found on the drive lever during the inspections required by paragraph (a), before further flight replace the affected lever (P/N NB-45-D-1823) with a new lever (P/N NB-45-D-2165) by incorporating Modification NB/M/394 in accordance with Britten- Norman Service Bulletin BN-2/SB.24 dated January 8, 1969, or later ARB-approved issue or an FAA-approved equivalent. (c) The repetitive inspections required by paragraph (a) may be discontinued after compliance with paragraph (b) has been accomplished. This amendment becomes effective March 17, 1970.
88-10-05: 88-10-05 LOCKHEED AERONAUTICAL SYSTEMS COMPANY-GEORGIA: Amendment 39-5913. Applies to Model 382 series airplanes, Serial Numbers 3946 through 4250, and 4299 through 4303, except those having outer wings installed to a configuration equivalent to Serial Number 4542 or subsequent; certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent severe damage to the lower surface panels of the outer wings, accomplish the following: A. Within the next 50 hours time-in-service after the effective date of this AD; or upon the accumulation of 11,000 flight hours total time-in-service for airplanes Serial Numbers 3946 through 4250, or 18,000 flight hours total time-in-service for airplanes Serial Numbers 4299 through 4303; whichever occurs later, perform an inspection of the outer wing lower surface panels 1, 2, 3, and 4, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987, to determine the existence of doublers on those panels between outer wing stations 161 and 195. B. If doublers have been installed on panels 1, 2, 3, and 4, left and right, in accordance with Northwest Industries (NWI) Drawing 3609103, the airplane may be returned to normal service. C. If doublers have been installed on panels 1 and 2 in accordance with Lockheed Service Bulletin 382-152 (382-57-35), dated September 2, 1987, or later FAA-approved revisions, prior to further flight, accomplish either of the following: 1. Inspect the heat shield and nacelle fairing attachment fastener holes from outer wing station 161 to 195, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987. a. If no cracks are found, repeat this inspection at intervals not to exceed 300 flight hours. b. If cracks are found, prior to further flight, repair in accordance with an FAA-approved method. 2. Modify the wing in accordance with Lockheed Service Bulletin 382-57- 73, dated January 28,1988. Installation of this modification constitutes terminating action for the repetitive inspections required by paragraph C.1.a., above. D. If doublers have not been installed on panels 1, 2, 3, and 4, prior to further flight, accomplish either of the following: 1. Inspect the heat shield and nacelle fairing attachment fastener from outer wing station 161 to 195, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987. a. If no cracks are found, repeat this inspection at intervals not to exceed 300 flight hours. b. If cracks are found, prior to further flight, repair in accordance with an FAA approved method. 2. Modify the wing in accordance with Northwest Industries (NWI) Drawing 3609103. Installation of this modification constitutes terminating action for the repetitive inspections required by paragraph D.1.a., above. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes toa base in order to comply with the requirements of this AD. F. 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, Atlanta Aircraft Certification Office, FAA, Central Region. NOTE: The request for alternate means of compliance should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Atlanta Aircraft Certification Office. All persons affected by this directive who have not already received the applicable service information from the manufacturer may obtain copies upon request to Lockheed Aeronautical Systems Company-Georgia, Attn: Commercial and Customer Support, Department 72-05, Zone 80, 86 South Cobb Drive, Marietta, Georgia 30063. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia. This amendment becomes effective May 25, 1988.
2016-13-09: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. This AD was prompted by a determination that certain maintenance tasks for the horizontal stabilizer trim actuator (HSTA) are inadequate. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new airworthiness limitations for the HSTA. We are issuing this AD to detect and correct premature wear and cracking of the HSTA, which could result in failure of the HSTA and consequent loss of control of the airplane.
2016-14-08: We are superseding Airworthiness Directive (AD) 2015-10-03 for certain Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2015-10-03 required a detailed inspection for visible chrome of each affected main landing gear (MLG) sidestay upper cardan pin, associated nuts, and retainer assembly; pin replacement if needed; measurement of cardan pin clearance dimensions (gap check); corrective actions if necessary; and a report of all findings. This new AD requires a detailed inspection of the upper cardan pin and nut threads for any corrosion, pitting, or thread damage, and if necessary, replacement of the cardan pin and nut. This new AD also revises the applicability to include additional airplane models. This AD was prompted by a report that an MLG sidestay upper cardan pin migration event had been caused by corrosion due to lack of jointing compound and inadequate sealant application during the MLG installation. We are issuing this ADto detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing gear collapse and consequent damage to the airplane and injury to occupants.
58-09-02: 58-09-02 HARTZELL: Applies to HC-82XF-1 and -1A Propellers Installed on Cessna 180 Aircraft. Compliance required as outlined. There have been several reported instances of the piston guide rod P/N A-811 used in jack assembly B-804 breaking at the point where it is pinned to the A-96A fork. Failure of a guide rod will allow the particular blade to become uncontrollable. In view of the possible serious consequences resulting from vibration and the loss of control of the propeller, the following steps must be taken: 1. Inspection within 25 hours. If item 2 will not be complied with within 25 hours of operation, remove fork pin P/N A- 522 and slide the pitch change fork P/N A-96 sufficiently to completely expose the hole in push rod P/N A-811 used in jack assembly B-804. Visually inspect the exposed rod for cracks. If a crack is found, the rod should be removed from the propeller and replaced. 2. Replacement. Prior to September 1, 1958, replace jack assembly B-804 with jack assembly B-828. (Hartzell Service Bulletin No. 39 dated January 16, 1957, covers this same subject, and Hartzell Service Bulletin No. 47 also applies.)
82-09-01: 82-09-01 TELEDYNE CONTINENTAL MOTORS: Amendment 39-4412. Applies to the following engines installed in, but not limited to, Cessna Models 340 and 414 series airplanes: NEW ENGINES: TSIO-520-NB serial numbers 519735 thru 519738, 519781 thru 519785, 519885 thru 519890, 519893 thru 519897, 519899 through 519915, 519929 thru 519933, 519935 thru 519937, 519939 thru 519962, 521026 thru 521045, 521049 thru 521074, 521085 thru 521088, 521097, 521141 thru 521168, 521170 thru 521183, 521187 thru 521237, 521239 thru 521247, 521249 thru 521255, 521257, 521258, 521260 thru 521281, 521284 thru 521305, 521307 thru 521335, 521339, 521340, 521342 thru 521345, 521347, 521349, 521351, 521353, 521354, 521357, 521358, 521362, 521365, 521366, 521371, 521378, 521384, 521385, 521393, 521395, 521398, 521413 thru 521418, 521441, 521442, 521455, 521461. REBUILT ENGINES: TSIO-520-J serial numbers 218830, 218831, 218836, 218838 thru 218873; TSIO- 520-K serial numbers 224563, 224565 thru 224573; TSIO-520-N serial numbers 228231, 228243, 228248 thru 228250, 228255, 228262 thru 228363, 228365 thru 228368, 228373; TSIO-520-NB serial numbers 233976, 233982, 233986, 233987, 233989 thru 234058, 234060 thru 234069, 234071 thru 234074, 234077, 234078. Compliance is required as indicated unless already accomplished. To prevent the possibility of a fuel leak which could result in an engine compartment fire, accomplish the following: A. Prior to next flight, activate the boost pump to static check the fuel pressure regulator inlet and outlet for leaks. Visually inspect in the area of the fuel pressure regulator for the presence of fuel stains. If either inspection indicates a leak or stains, comply with Paragraph B before further flight. If no leak or stain is evident, comply with Paragraph B within the next 10 hours of operation. B. Remove the fuel fittings from the regulator and inspect the thread bores in the regulator and the threads of the fittings. If the threads in the regulator appear damaged, cut, or chipped (when compared to a normal pipe thread), replace the fuel pressure regulator with a serviceable regulator of a like part number. Replace any damaged fittings. Prior to installing the fittings, clean the threads with clean degreaser, Loctite "LOQUIC PRIMER T" or equivalent, to be sure all oil and dirt is removed. Blow dry with dry compressed air. Apply Loctite Hydraulic Sealant 69 or 569 or equivalent sparingly 3/4 of the way around on the fitting threads only. To avoid contamination of the fuel cavity, do not apply sealant to the first thread. Install the fittings until tight (at least 3-5 threads engagement). Allow sealant to cure for 30 minutes before pressure testing. NOTE: Teledyne Continental Motors Service Bulletin No. M82-5, dated April 26, 1982, pertains to this subject. An equivalent method of compliance may be approved by the Chief, Atlanta Aircraft Certification Office, Federal Aviation Administration, ACE-115A, P.O. Box 20636, Atlanta, Georgia 30320. This amendment becomes effective July 8, 1982, as to all persons except those to whom it was made immediately effective by priority mail, issued April 16, 1982.
65-12-03: 65-12-03 MOONEY: Amdt. 39-74 Part 39 Federal Register May 28, 1965. Applies to Model M20E Aircraft, Serial Numbers 101 through 722 Equipped with Hartzell Propeller, HC-C2YK/7666-2 or CHC-C2YK/7666-2. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To avoid continuous propeller operation in the speed range where vibration stresses are high, accomplish the following: (a) Add the following operating limitation to the Airplane Flight Manual: "Avoid continuous operation between 2,100 and 2,350 r.p.m." (b) Mark engine tachometer with a red arc from 2,100 to 2,350 r.p.m., install Mooney decal P/N 150010-65, on tachometer bezel glass in accordance with Mooney Service Letter No. 21-127, dated April 15, 1965. This directive effective May 28, 1965.
2016-14-02: We are superseding Airworthiness Directive (AD) 2012-18-12 for certain Airbus Model A318, A319, and A320 series airplanes. AD 2012-18- 12 required modifying the off-wing escape slide (OWS) enclosures on the left-hand (LH) side and right-hand (RH) side of the fuselage. This new AD retains the requirements of AD 2012-18-12 and expands the applicability to all Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by reports that additional OWS part numbers have been affected. We are issuing this AD to prevent off-wing exits on the LH and RH sides of the fuselage from becoming inoperative. During an emergency, inoperative off-wing exits could impair the safe evacuation of occupants, possibly resulting in personal injuries.
71-05-01: 71-05-01 SIKORSKY: Amdt. 39-1157. Applies to S-61 Type Helicopters Certified in all Categories. Compliance required as follows: To preclude the possibility of failure of the S-61 Main Landing Gear Axle, P/N 6125-50115-0, unless already accomplished, inspect and replace the axle in accordance with paragraph 2, Accomplishment Instructions of Sikorsky Service Bulletin 61B25-3 dated 15 January 1971 or later FAA-approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Report results of above inspection in compliance with this AD to Chief, Engineering and Manufacturing Branch, FAA, Eastern Region (Reporting Approved by Bureau of the Budget under BOB No. 04-R0174.) Replacement axle P/N S6125-50115-2 has a service life of 242,550 landings. This amendment is effective February 23, 1971.
2004-02-03: This amendment adopts a new airworthiness directive (AD) for the specified Agusta S.p.A. (Agusta) model helicopters that requires modifying each passenger compartment sliding door (door) by applying a kit to replace the levers and links. This amendment is prompted by instances of a door inadvertently opening during flight due to the unstable configuration of the door. The actions specified by this AD are intended to prevent the inadvertent opening of a door during flight and loss of a passenger or other objects from the cabin.
2016-14-06: We are superseding Airworthiness Directive (AD) 2006-13-05 for certain Pacific Aerospace Limited Model 750XL (type certificate previously held by Pacific Aerospace Corporation Ltd.) 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 some critical rivets on the wing not being fully age-hardened and being installed in specific locations where reduction in rivet strength reduces wing strength. We are issuing this AD to require actions to address the unsafe condition on these products.
56-26-01: 56-26-01 LOCKHEED: Applies to Super Constellation 1049 Series Aircraft, LAC Serial Numbers 4501 Through 4565, 4572 Through 4647 and 4163 Through 4166. Compliance required as soon as possible but not later than the next block overhaul or major inspection period after parts become available. The relays housed within the generator feeder protection main relay box have been found capable of overheating at high generator output. This could become excessive when one or more generators become inoperative. This box contains the main DC bus, which is the tie-point of all primary electric power for the airplane. To minimize the probability of complete electrical outage in this vital area, greater heat transfer capability shall be provided either by installing a blower and replacing the existing interconnecting bus bars with new bus bars having increased cooling areas, or by an equivalent means approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. (Lockheed 1049 Service Bulletin No. 2838, dated August 20, 1956, contains FAA- approved rework information for compliance with this AD.) This airworthiness directive does not apply to aircraft equipped with two 11 KVA alternators. Revised July 25, 1962.
82-06-09: 82-06-09 CANADAIR: Amendment 39-4347. Applies to Canadair CL-600-1A11 airplanes, Serial Numbers 1002 and on, certificated in all categories. To prevent collapse of the landing gear caused by loss of the side stay strut reaction point, accomplish the following: 1. Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, visually inspect the right and left hand main landing gear side stay attachment pins for cracked or missing locking pins Dowty Rotol part number 200809689. Cracked or missing locking pins must be replaced with MS20392-1C41 Pin, Straight, Headed- Drilled Shank; MS24665-132 Pin, Cotter (Split); and AN960-6L Washer, prior to further flight. 2. Within the next 50 hours time in service after the effective date of this AD, Dowty Rotol part number 20080689 locking pins in the right and left hand main landing gear side stay attachment must be replaced with MS20392-1C41 Pin, Straight, Headed-Drilled Shank; MS24655-132 Pin, Cotter (Split); and AN960-6L Washer. After replacement, these locking pins must be visually inspected for cracks at intervals not to exceed 150 hours time in service. 3. The repetitive inspections of paragraph 2 may be discontinued upon the incorporation of an installation approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 4. Equivalent inspections and parts must be approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 5. Airplanes may be flown in accordance with FAR 21.197 to a maintenance base for the accomplishment of the inspections required by this AD. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the addresses listed above. These documents may also be examined at the FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective March 22, 1982.
2024-10-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-800 and A330-900 series airplanes. This AD was prompted by a report of a protective cap found still in place on the drain hole of a fire extinguishing pipe, and by further investigations indicating these caps may have remained on other airplanes. This AD requires a one-time general visual inspection (GVI) of the engine fire extinguishing pipe drain hole and, depending on findings, removal of the protective cap, 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.
2016-14-05: We are superseding Airworthiness Directive (AD) 2008-15-06 for certain Textron Aviation Inc. Models 175 and 175A airplanes (type certificate previously held by Cessna Aircraft Company). AD 2008-15-06 required checking the airplane logbook to determine if the original engine mounting brackets had been replaced. If the original engine mounting brackets were still installed, the AD required repetitively inspecting those brackets for cracks and replacing any cracked engine mounting bracket until all four original engine mounting brackets were replaced. Replacing all four original engine mounting brackets terminated the actions required in AD 2008-15-06. Since we issued AD 2008-15-06, we have determined that the applicability needs to be changed to add one serial number and remove another. This new AD retains the actions required in AD 2008-15-06 and changes the Applicability section. We are issuing this AD to correct the unsafe condition on these products.
54-10-01: 54-10-01 HAMILTON STANDARD: Applies to All Models 23260, 24260, and 34D Series Propellers Using Wedge Insert Type Low Pitch Assemblies. Compliance required as indicated. In order to preclude any possibility of reverse system malfunction caused by breakage of the servo piston shaft as a result of fatigue in highly stressed areas: 1. At the earliest opportunity, but not later than the first overhaul subsequent to June 1, 1954, dimensionally inspect the internal diameter of all 75361 and previous wedge insert type servo piston shafts for a maximum of 0.688 inch. 2. Magnetically inspect the stop return spring seat thread area of the shafts at the period specified in item 1 and at every overhaul subsequent to that period. (Hamilton Standard Service Bulletin No. 287, revised March 5, 1954, covers these same inspections.)
2016-12-51: We are publishing a new airworthiness directive (AD) for Airbus Helicopters Model AS332L2 and Model EC225LP helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD immediately prohibits flight of all Model AS332L2 and EC225LP helicopters. This AD is prompted by an accident involving an EC225LP helicopter in which the main rotor hub (MRH) detached from the main gearbox (MGB). These actions are intended to prevent failure of the main rotor system and subsequent loss of control of the helicopter.
2016-13-11: We are superseding Airworthiness Directive (AD) 2008-05-06 for certain The Boeing Company Model 737-100, -200, -300, -400, and -500 series airplanes. AD 2008-05-06 required repetitive inspections for fatigue cracking in the longitudinal floor beam web, upper chord, and lower chord located at certain body stations, and repair if necessary. This new AD requires, for certain airplanes, an inspection to determine if tapered fillers are installed, and related investigative and corrective actions if necessary. This AD was prompted by reports of cracks in the center wing box longitudinal floor beams, upper chord, and lower chord. We are issuing this AD to detect and correct fatigue cracking of the upper and lower chords and web of the longitudinal floor beams, which could result in rapid loss of cabin pressure. \n\n((Page 43476))
2024-21-01: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes. This AD was prompted by a report of cracks found in the rear spar lower cap forward leg and lower aft skin of the right wing, during investigation of a fuel leak. This AD requires repetitive inspections for any fuel leak or crack of the lower aft skins, external doublers, and rear spar lower caps of the left and right wings, and corrective actions and inspection reports if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2016-13-07: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS 365 N3 helicopters. This AD requires inspecting the cabin and cockpit for labels, placards, or markings that provide jettison procedure instructions for cabin doors, removing any labels, placards, or markings that are in an incorrect location, and installing placards where they are missing. This AD is prompted by the determination that placards had not been installed according to specifications on newly manufactured helicopters. The actions are intended to provide exit procedures during an emergency.
2004-01-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and 0100 series airplanes. This AD requires a one-time general visual inspection of the left and right sides of the pedestal side cover adjacent to the rudder pedal on the cockpit floor for proper installation of the attachment bracket, and corrective actions if necessary. This action is necessary to prevent restricted movement of the rudder pedal due to a loose pedestal side cover causing interference, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
69-17-01: 69-17-01 MCDONNELL DOUGLAS DC-9 and BOEING 737: Amdt. 39-819. Applies to DC-9 airplanes equipped with AiResearch Model GTCP85-98D Auxiliary Power Unit (APU) Serial Numbers listed in AiResearch Telegraphic Bulletin No. 49A1761 dated July 1, 1969, or later FAA approved revision, and to Boeing 737 airplanes equipped with AiResearch Model GTCP85-129 APU serial numbers listed in AiResearch Telegraphic Bulletin No. 49A1760 dated July 1, 1969, or later FAA approved revision. \n\n\tCompliance required as indicated unless already accomplished. \n\n\tBecause of possible failure of the second stage impeller blades, the auxiliary power unit shall not be used as an alternate electric power source in place of a main engine driven generator until deficient impellers have been replaced. Pending replacement of the auxiliary power unit impeller, accomplishment of the following is required. \n\n\t1.\tWithin 10 hours time in service after the effective date of this Airworthiness Directive, install a placard in full view of the pilot to read: \n\n\tBoth main engine driven generators must be operative for takeoff. Only during in-flight emergency may the auxiliary power unit be used as an alternate electric power source. \n\n\t2.\tThis placard may be removed when the APU is replaced with an APU having satisfactory impeller blades, or when the APU is modified to incorporate an impeller with satisfactory impeller blades in accordance with the above AiResearch Telegraphic Service Bulletins. \n\n\tNOTE: Compliance with the inspection and speed reduction adjustments in these bulletins is optional. \n\n\tThis amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated July 3, 1969.
2016-13-06: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by reports of ruptured horizontal stabilizer de-icing boots. This AD requires a revision of the applicable airplane flight manual (AFM), repetitive inspections of the horizontal stabilizer de-icing boots, and applicable corrective actions. We are issuing this AD to detect and correct damage of the de- icing boot; such damage could lead to a ruptured boot, severe vibrations, and possible reduced control of the airplane.
83-08-06: 83-08-06 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-4636. Applies to Lockheed Model L-1011-385-3 series airplanes, certificated in all categories. Compliance is required as indicated, unless previously accomplished. To minimize the potential for a total loss of the Active Control System (ACS) inflight, accomplish the following by June 30, 1983: A. Modify the aircraft wiring in accordance with Part 2, Accomplishment Instructions, in Lockheed-California Company L-1011 Service Bulletin 093-22-147 dated August 17, 1982, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Alternative means of compliance providing an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, 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 in order to comply with the requirements of this AD. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. 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. This amendment becomes effective June 2, 1983.