Results
82-23-07: 82-23-07 RATIER-FIGEAC FH.146: Amendment 39-4490. Applies to Ratier-Figeac propeller Model FH.146. Compliance required within the next 100 hours of operation after the effective date of this AD unless already accomplished. To preclude the possibility of propeller blade failure, accomplish the following: (a) In accordance with Ratier-Figeac Service Bulletin No. 61-142 dated June 1, 1982, or an equivalent method approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, New England Region: 1. Measure electrical resistance at end of disconnected wires of slip ring assembly. 2. Measure electrical resistance of insulation between wires and each propeller blade. (b) Remove propellers with measurements outside the limits of Bulletin No. 61-142 from service prior to further flight. This airworthiness directive becomes effective November 15, 1982.
55-23-02: 55-23-02 LOCKHEED: Applies to Models 1049C, D, E, and G, Serial Numbers 4163 Through 4166, 4520 Through 4581, 4583 Through 4605, 4608 Through 4615, and 4620. Compliance required as indicated. 1. Inspect the outer wing main beam web between wing Stations 510 and 668 left and right for cracks as soon as practical and repeat at 125-hour intervals until reinforcement in accordance with paragraph 2 is accomplished. If cracks are found repair immediately in accordance with Lockheed Repair Manual, Report 8882, and continue 125-hour inspections until reinforcement per paragraph 2 is accomplished. Inspection for fuel stains alone as an indication of a crack is not sufficient because of the presence of fuel sealant on the forward side of the web. 2. To be accomplished as soon as possible, but not later than next scheduled progressive overhaul time, and in no case later than December 1, 1956, whichever occurs first: Reinforce the main beam web, left and right, between wing Stations510 and 668. This shall be accomplished by the addition of three extruded 75S-T6 stiffeners, (LS2186 or LS6097) or equivalent between each of the original stiffeners. The LS347-3 stiffeners added previously in accordance with AD 54-24-02 on some of these aircraft may be retained. In these cases, one new (LS2186 or LS6097 or equivalent) stiffener must be added between each of these and the original stiffeners in this area. (Lockheed Service Bulletin No. 1049/SB-2753 also covers this subject.)
2014-21-06: We are adopting a new airworthiness directive (AD) for certain Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400, 400A, 400T, and MU-300 airplanes. This AD was prompted by a report of a failure of the Acme nut threads in a pitch trim actuator (PTA). This AD requires an inspection to determine if PTAs having a certain serial number and part number are installed, and replacement if they are installed. This AD also requires repetitive replacements of PTAs with new PTAs or certain overhauled PTAs. We are issuing this AD to prevent failure of the Acme nut threads in the PTA, which could lead to loss of control of pitch trim and reduced controllability of the airplane.
2000-13-05: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc. (RR) RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This action requires initial and repetitive ultrasonic inspections for cracks in fan blade dovetail roots, and if necessary, replacement with serviceable parts. This amendment is prompted by reports of fan blade failures due to dovetail root cracks in factory engine. The actions specified in this AD are intended to prevent possible multiple fan blade failures, which could result in an uncontained engine failure and damage to the airplane.
2014-21-02: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model FU24-954 and FU24A-954 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 cracking of the control column at the wiring access hole, which could lead to loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
97-04-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires a visual inspection to determine if rudder disconnection has occurred, and replacement of the disconnect unit with a new disconnect unit, if necessary. This amendment is prompted by reports that, due to the existing design, the disconnect unit of the rudder disconnect system inadvertently opened on some airplanes. The actions specified by this AD are intended to prevent the disconnect unit from opening inadvertently, which could lead to inadequate rudder control, if the engine fails during take-off or go-around and if the airplane is at low speed.
2005-02-05: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections of installed LPC fan blade roots on-wing and during overhaul using a surface wave ultrasonic probe, and relubrication, according to accumulated life cycles. That AD also adds the application of Metco 58 blade root coating as an optional terminating action. This AD requires the same actions, but changes the reference to Mandatory Service Bulletin (MSB) No. RB.211-72-C879 from Revision 3 to Revision 4. This AD results from RR issuing MSB No. RB.211-72-C879, Revision 4, which contains revised Accomplishment Instructions and consumable materials list. We are issuing this AD to detect cracks in low pressure compressor (LPC) fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane.
80-14-10: 80-14-10 BRITTEN-NORMAN (BEMBRIDGE) LTD.: Amendment 39-3828. Applies to Model BN-2A Mark III Series Trislander airplanes, certificated in all categories. Compliance is required as indicated unless already accomplished. To detect corrosion and to prevent loss of the rudder mass balance arm brackets which could cause hazardous rudder flutter, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD or prior to 2 years since new, whichever occurs later, visually inspect for corrosion the support brackets of the mass balance arms at the top, and on each side, of the rudder in accordance with paragraph "ACTION," of Britten-Norman Service Bulletin BN-2/SB.116, dated June 5, 1978 (hereinafter referred to as the service bulletin), or an FAA-approved equivalent. (b) If corrosion is found as a result of the inspection required by paragraph (a) of this AD, before further flight, except that the aircraft may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where the work can be performed, accomplish either of the following: (1) Perform the permanent repair as specified in "Rectification - Part 1" of the service bulletin or an FAA-approved equivalent, and thereafter reinspect for corrosion in accordance with paragraph (a) of this AD, at intervals not to exceed 3 years from the date of the repair; or (2) Perform the temporary repair as specified in "Rectification - Part 2" of the service bulletin or an FAA-approved equivalent, and thereafter continue to perform the inspection required by paragraph (a) of this AD, at intervals not to exceed 2 months from the date of the repair, for a maximum of 1 year at which time the permanent repair and inspection required by paragraph (b)(1) of this AD must be accomplished. (c) If no external corrosion is found as a result of the inspection required by paragraph (a) of this AD, the mass balance arm support brackets may continue in servicefor a period not to exceed 6 months from the date of the initial inspection, provided that the visual inspection required by paragraph (a) of this AD is repeated at intervals not to exceed 2 months or 200 hours time in service from the last inspection, whichever occurs first, after which the permanent or temporary repairs and inspections of paragraph (b)(1) or (b)(2) must be accomplished. (d) Prior to the installation of rudders held in stock as spares, accomplish the inspection and repair as necessary in accordance with paragraphs (a) and (b)(1) of this AD. (e) For purposes of this AD, an FAA-approved equivalent must be approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium, Telephone: 513.38.30. This amendment becomes effective July 14, 1980.
80-20-06: 80-20-06 CESSNA: Amendment 39-3937. Applies to Model 421C airplanes (Serial Number 421C0401 and on) having King KFC-200 Flight Control System installed under Supplemental Type Certificate SA1246CE. COMPLIANCE: Required as indicated unless already accomplished. To prevent the airplane from exceeding 60 degrees bank angle in the event of a roll axis hard-over malfunction, accomplish the following: A) Within the next 25 hours time-in-service after the effective date of this AD, reset the KFC-200 roll axis slip clutch from 60 plus or minus 6 inch-pounds to 38 plus or minus 4 inch-pounds in accordance with the instructions contained in King Radio Service Sales Installation Bulletin No. 167 dated August 4, 1980. B) Airplanes may be flown in accordance with FAR 21.197 to a location where the maintenance required by this AD may be performed provided the autopilot is inoperative. C) Any equivalent method of compliance must be approved by the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective October 14, 1980.
2023-14-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. This AD was prompted by a determination that radio altimeters cannot be relied upon to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band), and a recent determination that this interference may affect other airplane systems using radio altimeter data, including the ground spoiler deployment system. This AD requires revising the limitations section of the existing AFM to incorporate limitations prohibiting the use of a certain master minimum equipment list (MMEL) item. The FAA is issuing this AD to address the unsafe condition on these products.
79-19-04: 79-19-04 SHORT BROTHERS LIMITED: Amendment 39-3552. Applies to Model SD3-30 airplanes, S/Nos. SH 3004, 3005, 3006, 3007, and 3008, certificated in all categories. Compliance is required prior to the accumulation of 10,000 flights or prior to the accumulation of 25 flights after the effective date of this AD, whichever occurs later, unless already accomplished; and thereafter at intervals not to exceed 10,000 flights. To prevent fatigue failure of the flap control rods, replace flap control rods, Part Nos. SD3-45-1853 and SD3-45-1855, located immediately aft of wing center section rear spar and part of inner flap mechanism, with new rods of identical part numbers in accordance with Section 2, "Accomplishment Instructions" of Short Brothers Ltd. Service Bulletin SD3-27-14, dated April 28, 1978, or an equivalent approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Region, Federal Aviation Administration, c/o American Embassy, Brussels,Belgium. For purposes of complying with this AD, a flight is defined as one takeoff and one landing. This amendment becomes effective October 4, 1979.
2000-12-08: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) Models CF6-80C2A1/A2/A3/A5/A5F/A8/D1F turbofan engines. This AD requires initial and repetitive visual inspections of left hand and right hand aft engine mount link assemblies for separations, cracks and spherical bearing race migration. Cracked or separated parts must be replaced prior to further flight. If spherical bearing race migration is discovered, an additional borescope inspection for cracks is also required. If no cracks are discovered by the additional borescope inspection, assemblies have a 75- cycle grace period for remaining in service before replacement. Finally, installation of improved aft engine mount link assemblies constitutes terminating action to the inspections of this AD. This amendment is prompted by a report of a fractured left hand aft engine mount link discovered during a scheduled removal of an engine of similar design. The actions specified by the AD are intended to prevent aft engine mount link failure, which can result in adverse redistribution of the aft engine mount loads and possible aft engine mount system failure.
2005-02-04: The FAA is adopting a new airworthiness directive (AD) for the McDonnell Douglas airplanes listed above. This AD requires identifying the part number of the cargo compartment smoke detectors and, if necessary, revising the Limitations section of the airplane flight manual to include procedures for testing the smoke detection system after the last engine is started. This AD also provides for the optional replacement of the subject smoke detectors with modified smoke detectors, which would terminate the operational limitation. This AD is prompted by a report indicating that the cargo smoke detectors can "lock up" during electrical power transfer from the auxiliary power unit to the engines. We are issuing this AD to identify and provide corrective action for a potentially inoperative smoke detector in the cargo compartment and ensure that the flightcrew is alerted in the event of a cargo compartment fire.
2000-12-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, A300-600, and A310 series airplanes, that currently requires inspections to detect cracks in the lower spar axis of the nacelle pylon between ribs 9 and 10, and repair, if necessary. The existing AD also provides for optional modification of the pylon, which terminates the inspections for Model A300 and A310 series airplanes and increases the threshold and repetitive interval of the inspections for Model A300-600 series airplanes. This amendment reduces the inspection threshold and requires repetitive inspections following accomplishment of the optional modification for Model A310 series airplanes. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking, which could result in reduced structural integrity of the lowerspar of the pylon.
2023-14-01: The FAA is superseding Airworthiness Directive (AD) 2023-06- 13, which applied to all Bombardier, Inc., Model BD-700-2A12 airplanes. AD 2023-06-13 required revising the existing airplane flight manual (AFM) with new limitations to mitigate identified hazards due to interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band) as identified by Notices to Air Missions (NOTAMs). Since the FAA issued AD 2023-06-13, the FAA determined that additional limitations are needed due to the continued deployment of new 5G C-Band stations whose signals are expected to cover most of the contiguous United States at transmission frequencies between 3.7-3.98 GHz. This AD requires revising the limitations section of the existing AFM to incorporate limitations prohibiting dispatch under certain master minimum equipment list (MMEL) items. The FAA is issuing this AD to address the unsafe condition on these products.
62-06-01: 62-06-01 BRANTLY: Amdt. 410 Part 507 Federal Register March 16, 1962. Applies to All Model B-2 Helicopters Equipped With Seat Back Adjustment Wire P/N B2-334-32. Compliance required within the next 10 hours' time in service after the effective date of this AD. To prevent the sudden movement of the seat backs to the full aft adjustment position, the following must be accomplished: Remove the seat back adjustment wire P/N B2-334-32 from the left and right seat backs. This directive effective March 23, 1962.
2000-12-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes. The AD requires installation of a modification of the thrust reverser control and indication system and wiring on each engine; and repetitive functional tests of that installation to detect discrepancies, and repair, if necessary. This amendment is prompted by the results of a safety review, which revealed that in-flight deployment of a thrust reverser could result in a significant reduction in airplane controllability. The actions specified by this AD are intended to ensure the integrity of the fail-safe features of the thrust reverser system by preventing possible failure modes, which could result in inadvertent deployment of a thrust reverser during flight, and consequent reduced controllability of the airplane.
98-20-38 R1: The FAA adopts a new airworthiness directive (AD) to revise AD 98-20-38, which applies to all Beech 200 series airplanes. AD 98-20-38 requires you to revise the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for and procedures for exiting from severe icing conditions. Part of the applicability of AD 98-20-38 includes the Raytheon Models B200 and B200C airplanes. AD 96-09-13 already requires AFM revisions on this subject for these airplane models. Consequently, FAA is revising AD 98-20-38 to remove the Models B200 and B200C from the applicability and add clarification that AD 96-09-13 affects these airplanes. We are issuing this AD to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations.
80-02-06: 80-02-06 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39- 3656. Applies to Fan Jet Falcon Series D, E and F airplanes, Serial numbers 1 through 404, certificated in all categories. Compliance is required as indicated, unless already accomplished. To reduce the possibility of flexible line failure in the engine fire extinguisher system, within the next 100 hours time in service after the effective date of this AD, unless already accomplished, in each engine fire extinguisher system, modify the rigid tubing and install a new flexible line in accordance with paragraph 2, "Accomplishment Instructions," of Avions Marcel Dassault, Service Bulletin No. 632, dated July 18, 1979, or an equivalent approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Region. This amendment becomes effective January 24, 1980.
2023-12-24: The FAA is adopting a new airworthiness directive (AD) for all GE Aviation Czech s.r.o. (GEAC) (type certificate previously held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Model M601E-11AS, M601E-11S, H75-100, H80-100, and H85-100 engines. This AD is prompted by reports of multiple failures of the needle bearing installed in propeller governors having part numbers (P/Ns) P-W11-1 or P-W11-2, caused by self-generated debris from the needle bearing, which led to oil contamination. This AD requires replacement of the affected propeller governors with a redesigned propeller governor and prohibits installation of the affected propeller governors, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
97-04-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pacific Scientific Company, HTL/Kin-Tech Division, fire extinguisher bottle cartridges (squibs), which may be installed on various transport category airplanes. This action requires a one-time inspection of the electrical receptacle of these fire extinguisher bottle cartridges and their mating connectors to detect the presence of aluminum foil in the area of the pins of the cartridges and the connectors, and removal of any aluminum foil that is present. This amendment is prompted by a report of failure of a fire extinguisher bottle cartridge to discharge as a result of the presence of aluminum foil in the cartridge, which caused electrical shorting of the pins. The actions specified in this AD are intended to prevent such shorting, which could result in failure of the fire extinguisher bottle to discharge when commanded.
2000-12-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that currently requires repetitive ultrasonic inspections to detect cracks in the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, and repair, if necessary. This amendment requires revising the compliance thresholds for the inspection and requires that the inspections be repeated at reduced intervals. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracks in the bolt holes of the wing spars, which could result in reduced structural integrity of a wing spar.
2014-19-04: We are superseding Airworthiness Directive (AD) 2004-03-19, which applies to certain Airbus Model A320-111, -211 and -231 series airplanes. AD 2004-03-19 required repetitive inspections for cracking in the transition and pick-up angles in the lower part of the center fuselage area, and corrective action if necessary. AD 2004-03-19 also provided for an optional terminating modification for the repetitive inspection requirements. This new AD requires accomplishing the modification by installing washers between the transition pick-up angle and the pin nuts, and doing related investigative and corrective actions if necessary. This new AD also adds airplanes to the applicability of AD 2004-03-19. This AD was prompted by a determination that the optional terminating modification must be required in order to address the unsafe condition. We are issuing this AD to prevent fatigue cracking in the transition and pick-up angles of the lower part of the center fuselage, which could resultin reduced structural integrity of the wing-fuselage support and fuselage pressure vessel.
97-04-13: This amendment adopts a new airworthiness directive (AD) that applies to Mitsubishi Heavy Industries, Ltd., (Mitsubishi) MU-2B series airplanes. This AD requires removing the vent check valve assembly from the bulkhead between the fuel tanks. This AD results from an incident where both engines on an affected airplane failed near the end of a flight because of lack of fuel to the engines. The incident is attributed to the fuel filler caps on the top of the wings not sealing correctly. The actions specified by this AD are intended to prevent the inability of both engines to utilize the entire fuel supply because of the outboard fuel not transferring to the center tank, which could result in an uncommanded engine shutdown.
79-15-01: 79-15-01 CESSNA: Amendment 39-3517. Applies to: Model 205 (210-5) Series (Serial Numbers 641, 205-0001 through 205-0577) airplanes; Model 206 (Serial Numbers 206-0001 through 206-0275) airplanes; Model U206/TU206 Series (Serial Numbers U206-0276 through U206-1444, U20601445 through U20604287, U20604289, U20604290, U20604292 through U20604335, U20604337 through U20604389, U20604391 through U20604787, U20604789 through U20604894, U20604896 through U20604906, U20604908 through U20604911, U20604913 through U20604958, U20604960 through U20604963, U20604965 through U20604973, U20604975 through U20604977, U20604980 through U20604985, U20604987 through U20604990, U20604992, U20604993, U20604995 through U20604998, U20605000 through U20605018, U20605020 through U20605058, U20605060, U20605061, U20605063, U20605066, U20605069, U20605071 through U20605073, U20605075, U20605077, U20605078, U20605083, U20605085, U20605086, U20605088, U20605095, U20605097, U20605100, U20605102, U20605105, U20605107 and U20605110) airplanes; Model P206/TP206 Series (Serial Numbers P206-0001 through P206-0603, P20600604 through P20600647) airplanes; Model 207/T207 Series (Serial Numbers 20700001 through 20700530) airplanes; Model T210 Series (Serial Numbers T210-0001 through T210-0454) airplanes; Model 210/T210 Series (Serial Numbers 21057841 through 21063013, 21063015 through 21063086, 21063088 through 21063228, 21063230 through 21063287, 21063289 through 21063298, 21063300 through 21063324, 21063326 through 21063389, 21063391 through 21063393, 21063396 through 21063399, 21063401, 21063403 through 21063407, 21063412, 21063413, 21063419, 21063424 and 21063426) airplanes; Model P210 Series (Serial Numbers P21000001 through P21000255, P21000257 through P21000273, P21000275 through P21000279, P21000281 through P21000283, P21000287, P21000290 and P21000292) airplanes. COMPLIANCE: Required as indicated unless already accomplished. To provide instructions for recognition of fuel system vapor blockage and operating procedures to restore normal fuel flow, within the next 25 hours time-in-service after the effective date of this AD, accomplish the following: A) On Model 205 (210-5) series (Serial Numbers 641, 205-0001 through 205-0555); Model 206 (Serial Numbers 206-0001 through 206-0137); Model 210 (Serial Numbers 21057841 through 21058351) airplanes, examine the airplane and its maintenance record to determine whether Cessna Service Kit SK 205-5 or SK 206-2 has been installed. If neither of these kits is installed, make an entry in the maintenance records indicating this AD is not applicable to the airplane and no further action is required. If Cessna Service Kit SK 205-5 or SK 206-2 has been installed, accomplish Paragraphs B) 1 and 2 of this AD. B) On affected (see Applicability Statement) Model 205 (210-5) series airplanes having serial numbers between 205-0556 through 205-0577 inclusive, Model 206 series airplanes having serial numbers between 206-0138 through 206-0275 inclusive, Model U206/TU206 series airplanes having serial numbers between U206-0276 through U206-1444 inclusive and U20601445 through U20604649 inclusive, Model P206/TP206 series airplanes having serial numbers between P206-0001 through P206-0603 inclusive and P20600604 through P20600647 inclusive, Model 207/T207 series airplanes having serial numbers between 20700001 through 20700482 inclusive, Model 210/T210 series airplanes having serial numbers between 21058352 through 21062954 inclusive, Model T210 series airplanes having serial numbers between T210-0001 through T210-0454 inclusive and Model P210 series airplanes having serial numbers between P21000001 through P21000150 inclusive; 1. Install Cessna P/N 1205252-2 placard next to the fuel flow indicator which reads as follows: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP - ON, ADJUST MIXTURE. 2. SELECT OPPOSITE TANK. 3. WHEN FUELFLOW STEADY, RESUME NORMAL OPERATIONS. SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS." 2. Place Cessna special procedure card P/N D1189-13 in the airplane at a location accessible to the pilot at all times when he is in the pilot's seat and revise the aircraft Equipment List by adding this card as a required item of equipment. C) On affected (See Applicability Statement) Model U206/TU206 series airplanes having serial numbers between U20604650 and U20605110 inclusive, Model 207/T207 series airplanes having Serial Numbers between 20700483 through 20700530 inclusive, Model 210/T210 series airplanes having Serial Numbers between 21062955 through 21063426 inclusive and Model P210 series airplanes having Serial Numbers between P21000151 through P21000292 inclusive; 1. Install Cessna P/N 1205252-1 placard next to the fuel flow indicator which reads as follows: "MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES 1. AUX FUEL PUMP - ON, ADJUST MIXTURE.2. SELECT OPPOSITE TANK. 3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS. SEE P.O.H. FOR EXPANDED INSTRUCTIONS." 2. Revise the Pilot's Operating Handbook for the following airplanes by inserting the revision specified below: Airplane Model Revision Cessna Part Number U206G Rev 1 22 May 1979 D1147R1-13PH TU206G Rev 2 22 May 1979 D1148R2-13PH 207A Rev 1 22 May 1979 D1149R1-13PH T207A Rev 2 22 May 1979 D1150R2-13PH 210N Rev 3 22 May 1979 D1151R3-13PH T210N Rev 3 22 May 1979 D1152R3-13PH P210N Rev 3 22 May 1979 D1153R3-13PH D) The modification required by this AD may be accomplished by owner/operator authorized to perform preventative maintenance under FAR 43. An entry should be made in the aircraft maintenance record indicating compliance; i.e., "AD 79-15-01 complied with by installing placard P/N 1205252-2 and Special Procedure Card P/N D1189-13 this date _________" or "AD 79-15-01 complied with by installing placard P/N 1205252-1 and Pilot's Operating Handbook Rev _____ dated _______, Cessna P/N _______ this date ___________." E) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. F) Any equivalent method of compliance with this Airworthiness Directive must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region, 601 E. 12th Street, Kansas City, Missouri 64106. Cessna Service Letter SE 79-25, dated April 30, 1979, and Supplement No. 1 thereto dated June 4, 1979, pertains to the subject matter of this Airworthiness Directive. Cessna Aircraft Company has mailed copies to all owners of record. Additional copies may be obtained from: Cessna Aircraft Co., Marketing Division, Attn: Customer Service Department, Wichita, Kansas 67201; Telephone (316) 689-9111. This Amendment becomes effective July 26, 1979.