Results
94-25-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Precision Airmotive Corporation (formerly Facet Aerospace Products and Marvel-Schebler) Model HA-6 series carburetors, that requires a modification in those carburetors not equipped with a mixture control retainer clip. This amendment is prompted by eight reports of excessive retention screw wear causing rough engine operation or engine power loss on engines equipped with a Model HA-6 series carburetor between January 1986 and August 1992. The actions specified by this AD are intended to prevent the interruption of fuel flow to the engine caused by the mixture control shaft moving out of position because of excessive wear of the mixture control shaft retention screw.
2020-21-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 airplanes. This AD was prompted by reports that the latches for the forward and aft pressure relief doors could be opened during exposure to fire, leading to a breach in the engine core firewall. This AD requires modification and re-identification of the affected thrust reversers (TRs) and latch access doors (LADs), 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.
60-10-03: 60-10-03\tBOEING: Amdt. 144 Part 507 Federal Register May 7, 1960. Applies to the following 707 series aircraft only: Serial Numbers 17586 through 17596, 17609 through 17612, 17628 through 17648, 17658 through 17672, 17696 through 17702, 17925 through 17927. \n\tCompliance required as indicated. \n\n\tAs a result of one known incident wherein aggravated dutch roll was experienced due to improper rigging of the outboard aileron balance tab, the following modifications shall be accomplished: \n\n\tUnless already accomplished, prior to July 1, 1960: \n\n\t(a)\tReplace aileron quadrant rod assembly P/N 90-2480-3001 with redesigned rod assembly P/N 69-10829 (LH and RH side). \n\n\t(b)\tReplace support channel P/N 6-83872-2000 located on beam installation P/N 9- 65133 (aileron lockout crank) with new channel P/N 69-10833. Adjust stop in accordance with maintenance manual procedure. \n\n\t(c)\tRevise rigging of outboard aileron balance tab to 1.5 degrees (plus-minus 0.5 degrees) down with the aileron in the neutral position. \n\n\t(Boeing Service Bulletin No. 583 dated September 24, 1959, pertains to this same subject.)
83-19-01: 83-19-01 PIPER: Amendment 39-4727. Applies to Model PA-38-112 (S/Ns 38-78A0001 thru 38-82A0122) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent possible inflight failure of the fin and stabilizer attachment because of fatigue damage, accomplish the following: a) Within the next 25 hours time-in-service on airplanes that have 500 or more hours time-in-service on the effective date of this AD, or upon the accumulation of 525 hours time-in-service on airplanes that have less than 500 hours time-in-service on the effective date of this AD, and at intervals not exceeding 100 hours time-in-service thereafter: 1) Inspect and, if necessary, repair or modify the forward and aft fin spars in accordance with the directions and criteria contained in the INSTRUCTIONS section of Piper Service Bulletin No. 763A dated July 25, 1983. b) The repetitive inspections required by this AD may be discontinued upon the incorporation of Piper Kit No. 764 965. c) The interval between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. e) An equivalent method of compliance with this AD may be used if approved by the Manager, New York Aircraft Certification Office, FAA, Room 202, 181 South Franklin Avenue, Valley Stream, New York 11581. This amendment becomes effective on September 29, 1983.
80-11-08: 80-11-08 BOEING VERTOL (VERTOL): Amendment 39-3778. Applies to Vertol Model 107-II helicopters with pilot or copilot cyclic stick boots, P/Ns 107S2226-9, -13 or -17, certificated in all categories. To prevent possible restriction of cyclic stick travel accomplish the following within the next 25 hours in service after the effective date of this AD, unless already accomplished. a. Loosen the velcro tape and camloc fasteners securing the pilot and copilot cyclic stick boots, P/N 107S2226-9, -13 or -17, and remove the boots. b. Remove the two rivets which attach the forward spring, P/N 107S2226-12, to the forward end of the boot base and discard the forward spring. c. Install washers and new rivets to plug the resulting two empty holes in the boot base. d. Reinstall the pilot and copilot stick boots. e. Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective May 28, 1980.
2009-12-16: We are superseding an existing airworthiness directive (AD) for the products listed above. 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: The manufacturer reported findings of missing primer on the internal of the elevator and rudder of aircraft S/N 8200. The aircraft S/N 8200 was with RUAG for maintenance purposes. Investigation performed by RUAG showed that the paint removal procedure for the rudder and elevator was changed from a paint stripping with brush and scraper to a procedure where the parts were submerged in a tank filled with hot liquid stripper. The stripper is called TURCO 5669 from Henkel Surface Technologies. The stripping process is described in the Technical Process Bulletin No. 238799 dated 09/01/1999. This paint stripping process change was not communicated to andnot approved by the TC-Holder. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-21-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that sticking effects have been observed affecting the breathing bag on certain passenger oxygen masks. This AD requires replacement of affected passenger oxygen masks, 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.
83-06-01: 83-06-01 BOEING: Amendment 39-4589. Applies to Boeing Model 767 Series Airplanes certificated in all categories. To prevent loss of engine throttle control due to power lever cable icing, accomplish the following within 30 days from the effective date of this AD, unless already accomplished. \n\tA.\tInstall ice shields on the number 6 and 7 slats per Boeing Service Bulletin 767-30-2, dated December 13, 1982, or later FAA approved revision. \n\tB.\tSpecial flight permits may be issued in accordance with FAR 21.199 to operate airplanes to a base for the accomplishment of this AD. \n\tC.\tAlternate means of compliance with the AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tThis amendment becomes effective April 4, 1983.
2003-21-07: The FAA is adopting a new airworthiness directive (AD) for certain The Cessna Aircraft Company (Cessna) Model 525 airplanes. This AD requires you to disengage the pitch trim circuit breaker and AP servo circuit breaker and then tie strap each of them to prevent them from being engaged. This AD is the result of analysis that reveals the potential for a single-wire shorting to 28 volts or a failure of a relay in the electric pitch trim system such that the relay contacts remain closed. We are issuing this AD to correct this single-point failure in the electric pitch trim system, which will result in a runaway pitch trim condition where the pilot could not disconnect using the control wheel autopilot/trim disconnect switch. Failure of the electric trim system would result in a large pitch mistrim and would cause excessive control forces that the pilot could not overcome.
94-24-06: This amendment adopts a new airworthiness directive (AD), applicable to all Raytheon Corporate Jets Model BH/HS 125-600A and -700A series airplanes, that requires installation of two new circuit breakers in the 6 volt output circuits of the flight deck lighting transformers on electrical Panel 'RY,' below the right pilot's seat. This amendment is prompted by a report of smoke in the flight deck due to a lighting transformer 6 volt output circuit short circuiting to ground. The actions specified by this AD are intended to prevent smoke or fire in the flight deck due to inadequate circuit protection for 6 volt circuits of the flight deck lighting transformer.
61-20-01: 61-20-01 AUTO CRAT MANUFACTURING COMPANY SAFETY BELT: Amdt. 341 Part 507 Federal Register September 23, 1961. Applies to All Aircraft Equipped With Auto Crat Model BN 1-1700 Series Safety Belts. Compliance required within the next 25 hours' time in service after the effective date of this AD. It has been determined by static test that the Auto Crat safety belt Model BN 1-1700 assemblies manufactured under Technical Standard Order C22 standards do not meet the minimum strength requirements of this TSO. Accordingly, these belt assemblies must either be replaced with belt assemblies that conform to TSO-C22 standards, or be reworked to incorporate a steel frame buckle BN 1-2000AW supplied by Auto Crat, or equivalent. When this steel frame buckle is installed, the modified belt assembly becomes Model BN 1-2000, which meets the TSO requirements and shall be marked with the new model number. (Auto Crat letters to various air carriers dated May 10, 1961, pertains to the same subject.) This directive effective October 24, 1961.
2020-20-09: The FAA is superseding Airworthiness Directives (ADs) 2015-14- 07, 2016-07-10, and 2016-24-09. AD 2015-14-07 applied to certain The Boeing Company Model 787-8 airplanes. AD 2016-07-10 and AD 2016-24-09 applied to all The Boeing Company Model 787-8 and 787-9 airplanes. ADs 2015-14-07, 2016-07-10, and 2016-24-09 required actions related to certain flight control module (FCM) software. This AD requires installing flight control electronics (FCE) common block point 5 (CBP5) software, which terminates the requirements of the ADs superseded by this AD. This AD was prompted by certain deficiencies in the FCM software, including a report of an unannunciated dual symmetric inboard slat skew. The FAA is issuing this AD to address the unsafe condition on these products.
2003-21-04: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to inspect the right inboard forward flap bell crank for cracks, deformation, and missing/incomplete welds. If cracks, deformation, or missing/incomplete welds are found, the AD would require you to immediately replace the flap bell crank or temporarily incorporate certain flap limitations. This AD is the result of reports of cracks and missing/incomplete welds in the right inboard forward flap bell crank. We are issuing this AD to prevent failure of the right inboard forward flap bell crank due to cracks, deformation, or missing/ incomplete welds. Such failure could lead to damage to the flap system and surrounding structure and result in reduced or loss of control of the airplane.
61-25-01: 61-25-01 CESSNA: Amdt. 376 Part 507 Federal Register December 9, 1961. Applies to All Models 120, 140, and 140A Aircraft, On Which A Met-Co-Aire Tricycle Landing Gear (STC SA4-916) Has Been Installed. Compliance required as indicated. To correct an unsafe condition in the main gear the following shall be accomplished: (a) Within 20 hours' time in service after the effective date of this AD and at periods thereafter not to exceed 100 hours' time in service: (1) Tighten and torque to 50-70 inch-pounds the four AN 4 bolts (two on each side) which extend through the Cessna main gear wedges and the Met-Co-Aire support plate, P/N RD-1001C-11. Care should be taken to insure that the AN 365 stop nuts have not bottomed on the bolt threads before adequately tightening the wedge in place as specified above; use metal washers under the nut or bolt heads as necessary. (2) Conduct a close visual inspection for cracks in the corners of the slots in the support plate, P/N RD-1001C-11, and in the attach plate. Parts exhibiting evidence of cracks shall be replaced with Met-Co-Aire P/N RD-1001C-6 or FAA approved equivalent. When a new part is installed, the repetitive inspection prescribed in this subparagraph may be discontinued. (b) Within 20 hours' time in service after the effective date of this AD: (1) Inspect the attachment of the top flanges of the bulkheads in the landing gear attachment box and perform such work as necessary to assure that all rivets which secure the box to the floor structure are properly installed. Refer to Met-Co-Aire installation instructions dated August 29, 1959, as revised January 1, 1961, for description and location of necessary rivets. (2) If installed, remove the adapter plates, Cessna P/N 0441147, which may have been used to extend the main gear wheels forward. (Met-Co-Aire Service Directive SD-1003 covers this same subject.) This directive effective December 20, 1961.
81-13-09 R2: 81-13-09 R2 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39-4175 as amended by Amendment 39-4280. Applies to Models AS350 and AS355 Series Helicopters, certificated in all categories, that are equipped with tail rotor blade pitch horns, P/N 350A12-1368-01 or -02 (Airworthiness Docket No. 81-ASW-28). Compliance required as indicated. To detect possible cracks and prevent failure of the tail rotor blade pitch horns, accomplish the following: (a) Within 10 hours' time in service after the effective date of this AD, unless already accomplished per Aerospatiale Telex Service No. 01.07A dated June 5, 1981, remove each pitch horn, clean and remove paint, inspect for flatness and inspect for cracks as specified in Aerospatiale Telex Service No. 01.07A. (b) Replace horns before further flight if not flat or if cracked. (c) Serviceable pitch horns that comply with this AD must be reinstalled as specified in the Aerospatiale Telex Service No. 01.07A. (d) For pitch horns, P/N 350A-12-1368-01, after initial compliance with paragraphs (a) and (c) of this AD and prior to the first flight of each day, conduct the following: (1) Clean thoroughly, the surface of each horn at the two-mounting bolts. (2) Inspect each horn for cracks using a five power or higher magnifying glass and light in the area of the mounting bolt countersink or spotface and adjacent radii of the yoke. (3) If a crack is found, remove the affected horn prior to further flight and install a serviceable horn as specified in paragraph (c) of this AD. (e) Equivalent means of compliance must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (f) Special flight permits may be issued in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations to fly aircraft to a base where paragraphs (a) through (c) of this AD can be accomplished. (g) For pitch horns, P/N 350A12-1368-01, accomplish the following: (1) Horns with 400 hours' or more total time in service on July 31, 1981, remove from service within the next 50 hours' time in service. (2) Horns with less than 400 hours' total time in service on July 31, 1981, remove from service before attaining 450 hours' total time in service. (h) For pitch horns, P/N 350A-12-1368-02, remove from service on or before attaining 1,250 hours' total time in service. (i) AS350 Service Bulletin No. 01.07 Revision 2 and AS355 Service Bulletin No. 01.01 Revision 1 may be used instead of TELEX Service No. 01.07A. (Aerospatiale Telex Service No. 01.07B dated June 30, 1981, pertains to the 450 hour' limit.) Amendment 39-4175 became effective July 31, 1981, to all persons including those persons to whom it was made effective by priority mail AD No. 81-13-09 issued June 16, 1981, and to whom part of the amendment was made effective by priority mail AD 81-13-09 issued June 16, 1981. This amendment 39-4280 becomes effective December 18, 1981.
2020-20-16: The FAA is superseding Airworthiness Directive (AD) 2018-17- 05, which applied to all Airbus SAS \n\n((Page 63435)) \n\nModel A350-941 and -1041 airplanes. AD 2018-17-05 required a check of the insulation resistance of the direct drive solenoid valve (DDSOV) of each affected electro-hydrostatic actuator (EHA) and applicable corrective actions. Since the FAA issued AD 2018-17-05, it was determined that certain EHA part numbers can be modified and re- identified as specified in a European Union Aviation Safety Agency (EASA) AD, which could inadvertently remove certain part numbers from the applicability in other EHA-related ADs including AD 2018-17-05. This AD was prompted by reports of EHA units that were returned to the manufacturer with degraded insulation resistance in the DDSOV; investigation results revealed that moisture ingress, due to incorrect sealing application, had caused this degradation. This AD was also prompted by a report of a technical issue detected on EHAs installed on inboard ailerons and elevators, causing potential erroneous monitoring of those actuators. This AD requires a check of the insulation resistance of the DDSOV of each affected EHA and applicable corrective actions, and modification or replacement of certain EHAs; as specified in two EASA ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2020-20-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, EC155B1, AS350B3, AS355F, AS355F1, AS355F2, AS355N, AS355NP, EC130B4, and EC130T2 helicopters. This AD requires inspecting the main rotor (M/R) servo actuators, and depending on the inspection results, replacing the affected part, applying a slippage mark, and reporting information. This AD was prompted by an incident of a sudden, strong nose-up attitude followed by intensive vibrations and increased loads on the flight controls during a cruise flight. The actions of this AD are intended to address an unsafe condition on these products.
2003-21-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 airplanes, that currently requires a one-time detailed visual inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; and corrective action, if necessary. This amendment requires a new inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; repair if necessary; installation of a grommet around the lower edge of the feed-through; replacement of the support bracket with a new bracket; and relocation of the support clamp of the wire bundle; as applicable. The actions specified by this AD are intended to prevent the wire bundle contained in the feed-through from contacting the bottom of the feed-through, which could cause cable chafing, electrical arcing, and smoke or fire in the cockpit. This action is intended to address the identified unsafe condition.
80-21-01: 80-21-01 MCDONNELL DOUGLAS: Amendment 39-3933. Applies to DC-10 Series Airplanes fuselage numbers 1 through 243. \n\n\tCompliance required as indicated, unless already accomplished. To prevent restriction of travel of the wing and tail engine fuel shutoff valve, thereby adversely affecting operation of the engine emergency fire shutoff handles and loss of associated fire fighting safeguards, accomplish the following: \n\n\t(a)\tWithin 300 hours additional time in service after the effective date of this AD replace P/N AA 2603 type cable guard pins in accordance with McDonnell Douglas Alert Service Bulletin A76-28 as dated September 8, 1980. \n\n\t(b)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. \n\n\t(c)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective October 13, 1980.
94-24-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, and -40 series airplanes, KC-10A (military) airplanes, and Model MD-11 series airplanes, that requires the installation of retainers and supports at the lateral control mixer bracket on the center of the wing rear spar of the airplane. This amendment is prompted by an analysis conducted by the manufacturer, which revealed that failure of a lateral control mixer bracket could result in uncommanded deployment of the spoiler. The actions specified by this AD are intended to prevent inadvertent asymmetric deployment of the spoiler, which may lead to reduced controllability of the airplane.
2021-10-17: The FAA is adopting a new airworthiness directive (AD) for certain Mooney International Corporation (Mooney) Model M20V airplanes. This AD was prompted by reports of short circuit and arcing of the alternator main power cable in the engine compartment. This condition, if unaddressed, could result in a fire hazard, loss of engine thrust control, and reduced control of the airplane. This AD requires inspecting the alternator main power cable and the exhaust crossover tube for damage, replacing damaged parts as necessary, and installing an additional alternator cable clamp. The FAA is issuing this AD to address the unsafe condition on these products.
80-13-51: 80-13-51 GROUPEMENT d'INTERET ECONOMIQUE AIRBUS INDUSTRIE (AIRBUS): Amendment 39-4010. Applies to Model A300B4-103 airplanes modified in accordance with Airbus Mod. 2150, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent possible operation at degraded performance levels due to inaccurate performance data presented in the airplane flight manual (AFM), accomplish the following: (a) Prior to further flight, except that the airplane can be ferried in accordance with FAR Sections 21.197 and 21.199 to a place where replacement can be made, if CF-6-50C or CF- 6-50C1 engines are installed, replace with serviceable CF6-50C2 engines, and (b) Within 20 hours time in service after the effective date of this AD, incorporate Airbus Industrie A300B4-103 AFM, Revision 6, dated May 28, 1980, or an FAA-approved equivalent, into the airplane flight manual and operate the airplane accordingly. (c) If an equivalent meansof compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. This amendment becomes effective January 2, 1981, as to all persons except those persons to whom it was made immediately effective by telegraphic AD T80-13-51, issued June 18, 1980, which contained this amendment.
2003-21-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes. This action requires modifying the rear fuselage to reinforce a certain frame segment. This action is necessary to prevent fatigue cracking of the rear fuselage, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
94-22-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-8-70 series airplanes, that currently requires replacement of all attachment screws at the exhaust nozzle plug splice, and a check of nut plates for running torque and replacement of nut plates, if necessary. This amendment requires modification of the engine exhaust plug assemblies as terminating action for the currently required replacement and check. This amendment is prompted by reports of loose or missing attachments at the splice joint of the engine forward and aft exhaust plugs, and loss of the rear exhaust plug following an engine bird strike. The actions specified by this AD are intended to prevent reduced integrity of the engine exhaust plug installation, which may lead to separation of exhaust plugs from the airplane, and create a hazard to persons and property on the ground.
81-18-06: 81-18-06 FAIRCHILD: Amendment 39-4202. Applies to Model C-119 series airplanes certificated in all categories under various type certificates including, but not limited to Pacific International Foods, Inc., A6NW, William Waara, A32CE, Starbird, Inc., A5NW, Aero Union Corporation, A21WE, Hawkins and Powers, Inc., A24WE. Compliance required as indicated, unless already accomplished. To prevent possible wing failure due to loads induced by a free aileron, accomplish the following: (a) Within 100 hours' time in service or within 60 days from the effective date of this AD, whichever occurs earlier, conduct inspections of the inboard and outboard aileron, aileron control system, and all aileron attachment fittings of the outer wing panel using the applicable inspection instructions of Section III Wing Group and Section X Control Systems Group of USAF Technical Order T.O. 1C-119G-36 and additional inspection procedures given below. (b) Remove the left and right handinboard and outboard ailerons and inspect for evidence of cracks, corrosion, pitting; loose, distorted or corroded fasteners; excessive wear and elongated holes in accordance with the visual, dye penetrant and X-ray procedures of TO.O 1C-119G-36, paragraphs 3-25 through 3-36. (c) Inspect the aileron flight control linkage in the left and right hand wing outer panel for evidence of cracks, corrosion, pitting; loose, distorted or corroded fasteners; excessive wear and elongated holes in accordance with visual, magnetic and dye penetrant procedures of T.O. 1C-119G-36, paragraphs 10-11 through 10-14, with the following exceptions for the bellcrank item C-30 of T.O. 1C-119G-36. (1) Remove the left and right hand inboard aileron bellcrank assembly, P/N 110-727202-21 and P/N 110-727202-22, indicated as item C-30 in T.O. 1C-119G-36, Figure 10-3, page 10-25. (2) Conduct a dye penetrant inspection in accordance with T.O. 1C-119G-36, paragraph 10-14(c)(2), after removal ofthe bushings and bearings. Particular attention should be directed to the exterior and interior surfaces of the central hub of the bellcrank. (d) Using a 10X magnifier, inspect the truss support assembly which is attached to the upper and lower rear wing spar cap and inner aileron bellcrank inter-rib support bracket in left and right outer wing panels for evidence of corrosion, cracks or loss of structural integrity caused by erosion of tubular wall thickness. NOTE: Part numbers found on some C-119 model aircraft are P/N 78-135106-0005R and P/N 78-135106-0008L. (e) If any cracks, corrosion, pitting; loose, distorted or corroded fasteners; excessive wear or elongated holes are detected during the inspections, repair in accordance with T.O. 1C-119B-3 or replace with like serviceable part in accordance with the procedures of the applicable paragraphs in T.O. 1C-119G-36, prior to further flight. (f) Prior to return to service, after accomplishing other inspectionsrequired by this AD, conduct a balance inspection of all four ailerons per procedures specified in the applicable maintenance instructions. Any out-of-limit condition must be corrected prior to further flight. (g) Repeat the inspections required by paragraph (c), (d) and (f) of this AD at intervals not to exceed 3000 hours' time in service or one (1) year from the last such inspection, whichever occurs earlier. (h) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD. (i) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. (j) The 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 may obtain copies upon request to FAA Western Region Office, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its Headquarters in Washington, D.C. and at FAA Western Region Office. This amendment becomes effective September 10, 1981.