Results
99-04-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections of the outboard nacelle struts to detect fatigue cracking of the strut skin and spring beam support fittings, and to detect cracked or loose fasteners of the support fittings; and corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspection requirements. This amendment is prompted by reports indicating that several cracked or broken spring beam support fittings were found on the outboard nacelle struts. The actions specified by this AD are intended to detect and correct such fatigue cracking and loose fasteners, which could result in failure of the outboard nacelle struts and consequent separation of the engine.
57-10-01: 57-10-01 MOONEY: Applies to Model M-20 Aircraft Serial Numbers 1002 Through 1126 Incorporating Main Landing Gear Retracting Bellcrank Bracket P/N 5035. To be accomplished as soon as practicable but not later than July 1, 1957. Cracks have been reported in the main landing gear retracting bellcrank bracket P/N 5035. In one case complete failure of the bracket resulted in jamming the elevator control system. Therefore, it is required that bracket PN 5035 be replaced by new redesigned brackets P/N 5101 which have a 0.095 inch wall tubing. The revised retracting bellcrank bracket P/N 5101 incorporated a reinforcing angle at the lower front corner and a cross member between the gear bungee fittings. (Mooney Service Letter 20-22 covers this same subject.)
87-23-04 R1: 87-23-04 R1 ROLLS-ROYCE plc: Amendment 39-5753 as amended by amendment 39-6180. Applicability: Rolls-Royce plc (R-R) RB211-22B, -524, -524B, -524B2, -524B3, and -524C2 turbofan engines. Compliance: Required as indicated, unless already accomplished. To prevent low pressure turbine (LPT) stage 1 disk uncontained failure, accomplish the following: (a) Modify LPT stage 2 vane nozzle assemblies, Part Numbers (P/N) LK63392, LK63331, LK63333, LK59046, LK59816, LK59853, LK59818, LK59038, LK55447, LK55420, LK54278, LK55452, and LK59002, in accordance with the Accomplishment Instructions of R-R Service Bulletin (SB) RB.211-72-8301, Revision 5, dated May 13, 1988, at the next shop visit of the LPT module, but not later than June 30, 1989. NOTE: For the purpose of this AD, an LPT module shop visit is defined as separation of the LPT rotor assembly from the LPT case/vane nozzle assembly as necessitated by (1) its condition or (2) a requirement for scheduled maintenance. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD may be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, and 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, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service. The LPT stage 2 vane nozzle assembly modification shall be done in accordance with Rolls-Royce SB RB.211-72-8301, Revision 5, dated May 13, 1988. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552 (a) and 1 CFR Part 51. Copies may be obtained from Rolls-Royce plc, Technical Publications Department, P.O. Box 31, Derby DE2 8BJ, England. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, DC. Amendment 39-5753, AD 87-23-04 became effective on December 11, 1987. This amendment (39-6180, AD 87-23-04 R1) becomes effective on May 31, 1989.
99-03-04: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires installation of components to provide shielding and separation of the fuel system wiring (that is routed to the fuel tanks) from adjacent wiring. This amendment also requires installation of flame arrestors and pressure relief valves in the fuel vent system. This amendment is prompted by testing results, obtained in support of an accident investigation, and by re-examination of possible causes of a similar accident. The actions specified by this AD are intended to prevent possible ignition of fuel vapors in the fuel tanks, and external ignition of fuel vapor exiting the fuel vent system and consequent propagation of a flame front into the fuel tanks.
91-02-04: 91-02-04 GROB WERKE GMBH & CO. KG (GROB): Amendment 39-6823; Docket No. 90-CE-29-AD. Applicability: Models G103 "Twin Astir" (including "Trainer") gliders (Serial Numbers (S/N) 3000 through 3291) and G103 "Twin II" (including "ACRO") gliders (S/N 3501 through 3729), certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To preclude the incorrect installation of the aileron system connecting bolt, accomplish the following: (a) Modify the aileron control system by installing a GROB forkhead nut (GROB part number 103B-4229) and removing the placard that cautions against incorrect installation of the connecting bolts located on the aileron control lever adjacent to the connecting bolt, if installed, as described in GROB Service Bulletin No. TM 315-38/1, dated December 12, 1989. (b) An alternate method of compliance or adjustment of the compliance time thatprovides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium; Telephone (322) 513.38.30 ext. 2718; Facsimile (322) 230.68.99. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (c) All persons affected by this directive may obtain copies of the document referred to herein upon request to GROB Systems, Incorporated; Aircraft Division, I-75 and Airport Drive, Bluffton, Ohio 45817; Telephone (419) 358-9015; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6823, AD 91-02-04) becomes effective on February 8, 1991.
2013-16-16: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 and AB412 EP, and Bell Helicopter Textron (Bell) Model 412, 412CF, and 412EP helicopters with certain DART Aerospace Ltd. (Dart) high gear aft crosstubes (crosstube) installed. This AD requires adding a life limit of 10,000 landings to the crosstube and removing from service any crosstubes with more than 10,000 accumulated landings. This AD is prompted by five separate reports of crosstube failures. The actions in this AD are intended to prevent failure of the crosstube and subsequent collapse of the landing gear.
2010-14-06: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model 737-300, -400, and -500 series airplanes. That AD currently requires an inspection to determine the manufacturer and manufacture date of the oxygen masks in the passenger service unit and the lavatory and attendant box assemblies, corrective action if necessary, and other specified action. This new AD expands the applicability in the existing AD. This AD results from a determination indicating that additional airplanes may be subject to the identified unsafe condition. We are issuing this AD to prevent the in-line flow indicators of the passenger oxygen masks from fracturing and separating, which could inhibit oxygen flow to the masks and consequently result in exposure of the passengers and cabin attendants to hypoxia following a depressurization event.
2013-16-09: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and [[Page 48287]] A321 series airplanes. This AD requires an inspection to determine airplane configuration and part numbers of the landing gear control interface unit and main landing gear (MLG) door actuators; and, for affected airplanes, repetitive inspections of the opening sequence of the MLG door actuator, and replacement of the MLG door actuator if necessary. This AD also provides optional terminating action for the repetitive inspections. This AD was prompted by a report of a MLG failing to extend during landing, and a determination that a certain configuration of landing gear control interface unit and actuators may result in masking of centralized fault display system messages that are necessary to mitigate risks associated with failure of MLG extension or down-locking. We are issuing this AD to detect and correct such a configuration, which could prevent the full extension or down-locking of the MLG, possibly resulting in MLG collapse during landing and consequent damage to the airplane and injury to occupants.
2013-15-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a determination that certain flap actuators require restoration by installing a redesigned flap actuator inboard pinion seal. This AD requires revising the maintenance program by incorporating new airworthiness limitation tasks. We are issuing this AD to prevent flap system failure, and consequent reduced control of the airplane.
98-26-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-26-51 that was sent previously to all known U.S. owners and operators of certain McDonnell Douglas Model DC-8 series airplanes by individual telegrams. This AD requires a revision to the Airplane Flight Manual to specify restrictions on operating if any pressurization anomaly is detected. This AD also requires a one-time inspection to detect discrepancies and cracking of the main deck cargo door in the immediate area of the bolts attaching the latch fittings, and repair, if necessary. This action is prompted by a report that a cabin pressurization anomaly was detected on a McDonnell Douglas Model DC-8 series airplane, and by subsequent investigation, which revealed fatigue cracking in the structure of the main deck cargo door. The actions specified by this AD are intended to detect and correct fatigue cracking in the structure of the main deck cargo door, which could result in cabin decompression of the airplane and loss of the main deck cargo door, and consequent reduced controllability of the airplane.\n\n\tEffective February 3, 1999, to all persons except those persons to whom it was made immediately effective by telegraphic AD T98-26-51, issued December 18, 1998, which contained the requirements of this amendment. \n\n\tComments for inclusion in the Rules Docket must be received on or before March 30, 1999.
81-10-02: 81-10-02 HILLER AVIATION: Amendment 39-4103. Applies to all Models FH 1100 Series Helicopter, certified in all categories, Serial Nos. 001 through 254. Compliance required as indicated, unless already accomplished. To prevent the upper controls support column from contacting and damaging the main rotor mast accomplish the following: (a) Within the next ten (10) calendar days from the effective date of this AD (1) Accomplish a one time visual inspection of the support column P/N 24-30208 to determine whether or not the base flange P/N 24-30210 is undersized. Inspection is to be performed in accordance with Hiller Service Bulletin SB 30-9, Part 2, Subpart B, dated April 3, 1981. (2) If the inspection (a) (1) determines that the flange thickness is in accordance with type design (specifically 0.090 0.010 inches), no further AD action is required. (b) After inspection of paragraph (a) (1) and a determination that the flange thickness is undersized, prior to further flight (1) Replace the support column P/N 24-30208 with a like serviceable part which is in compliance with type design; and (2) Inspect the main rotor mast for damage (nicks, scratches or dents) at the top of the support column location, approximately 12.375 inches from top of upper housing of transmission. Replace each damaged main rotor mast with a like serviceable part. NOTE: The main rotor mast cannot be inspected until the upper controls and support column are disassembled. NOTE: Hiller kits P/N SBK-FH-1100-23-2 and spares stock may contain undersize flight control system support columns. (c) Verify that any replacement support column is in compliance with type design as noted in paragraph (a) (2) prior to return to service. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate helicopters to a base for the accomplishment of inspections and maintenance required by this AD. 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. 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. 553(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Hiller Aviation, 2075 West Scranton Avenue, Porterville, California 93275. These documents may also be examined at FAA Western Region Office, Room 6W14, 15000 Aviation Boulevard, Hawthorne, California 92061; 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 May 11, 1981.
91-10-10: 91-10-10 BRITISH AEROSPACE: Amendment 39-6995. Docket No. 91-NM-09-AD. Applicability: All Model BAe 125-800A series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a wheel loosening from the axle and the possible loss of a wheel, accomplish the following: A. Within 30 days after the effective date of this AD, inspect all nose wheels for nose wheel serial numbers, listed in paragraph 2.A.(2) of Dunlop Service Bulletin AH52339-A32-1046, dated July 27, 1990. B. If the serial number on the nose wheel coincides with any of the serial numbers listed in paragraph 2.A.(2) of Dunlop Service Bulletin AH52339-A32-1046, dated July 27, 1990, retorque the location plate retaining nuts to 8 foot-pounds in accordance with the service bulletin. NOTE: If the airplane maintenance records indicate that the nose wheel assembly has had the wheel halves disassembled and reassembled since the airplane was new, the required retorquing will have been accomplished at that time, and no further action is required. WARNING: DO NOT ADJUST THE TORQUE TIGHTENED MAIN HUB TIE BOLTS WITH THE TIRE INFLATED. C. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. 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 the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6995, AD 91-10-10) becomes effective on June 18, 1991.
62-17-03: 62-17-03 DOUGLAS: Amdt. 468 Part 507 Federal Register July 28, 1962. Applies to DC-8 Aircraft, Serial Numbers 45253-45289, 45291-45306, 45376-45382, 45384-45393, 45408-45413, 45416-45419, 45421-45431, 45433, 45442-45445, 45526, 45565-45570, 45588-45606, 45609-45614, 45617-45618, 45620-45622, 45624-45627. \n\n\tCompliance required within 300 hours' time in service after the effective date of this AD. \n\n\tInvestigation has shown that the overwing emergency exits cannot, under all necessary circumstances, be opened from outside the airplane, as required by Civil Air Regulations Sections 4b.362(e)(2) and 4b.362(e)(3). To eliminate this condition, one of the following modifications shall be accomplished with respect to each aft overwing exit which is not deactivated per Note 7 of Type Certificate Data Sheet 4A25 and with respect to each forward overwing exit: \n\n\t(a)\tThe outboard seat in the row of seats forward of each overwing exit shall be permanently blocked to prevent the seat from being reclined across any portion of the exit opening. The outboard seat in the row of seats aft of each overwing exit shall be permanently blocked to prevent the seat from being moved forward across any portion of the exit opening. \n\n\t(b)\tEach row of seats forward and aft of each overwing exit shall be relocated in an approved manner that will permit the exit door to be readily opened from the outside and removed when the back of the outboard seat in each such row of seats is in any of its possible positions. The seat track or other seat positioning means shall be clearly marked or blocked in a manner which will assure that these rows of seats are continuously retained in this position during service. \n\n\t(c)\tCombinations of the modifications specified in (a) and (b) may be used provided that fore and aft outboard seat backs are restricted from being placed in a position which will prevent opening of the exit from the outside. \n\n\t(d)\tRework each overwing exit door assembly,door jamb and lower stop, install a handle on the exterior of each of those door assemblies, and restrict the forward movement of the outboard seat in each row of seats just aft of an overwing exit. This total modification shall be such as to permit the exit door to be readily opened and removed from the outside when the backs of both adjacent outboard seats are in any of their possible positions. \n\n\t(Douglas DC-8 Service Bulletin No. 52-21 pertains to this same subject and describes an FAA approved means of complying with modification method (d).) \n\n\tThis directive effective August 27, 1962.
81-12-06 R1: 81-12-06 R1 BENDIX: Amendment 39-4249. Applies to Bendix Engine Products Division D-3000 and D-3200 (Blue) series magnetos identified as follows, unless previously identified by the letter "X", on the upper left area of magneto data plate: a. D-3000 series (see models specified under "MAGNETO IDENTIFICATION") pressurized (dark blue) magnetos with serial numbers below 1423, installed on AVCO Lycoming TIO, LTIO-540-J2BD engines. MAGNETO IDENTIFICATION MODEL PART NO. D6LN-3200 10-682910-13 D6RN-3200 10-682910-18 These magnetos are installed on but not limited to the following aircraft engines or aircraft engine/aircraft combinations: AVCO LYCOMING ENGINES AIRCRAFT INSTALLATIONS TIO-540-J2BD Piper PA-31-350; LTIO-540-J2BD STC SA1151SO and SA970SO Colemill conversion of Piper PA-31, PA-31-325 and PA-31-350; STC SA980NW Machen Industries conversion of Piper Aerostar 600 STC SA762NW Machen Industries conversion of Beechcraft Bonanza B35 and A36 series.To detect loose distributor gear rotating electrodes on magnetos having 100 hours or more in service since new or overhaul, accomplish paragraph c, before further flight, unless previously accomplished, and every 50 hours in service thereafter until the gears are replaced with laser welded gear assemblies identified by the presence of the letter "Z" or the letters "XO" on the retaining ring end of the gear axle. b. All D-3000 and D-3200 series (blue) magnetos with serial numbers 100 through 1968 not covered by paragraph a, unless previously accomplished. To detect loose distributor gear rotating electrodes on magnetos having 100 hours or more in service since new or overhaul, accomplish paragraph c, before the expiration of 50 hours in service since new or overhaul after the effective date of this AD unless previously accomplished and every 50 hours in service thereafter until the gears are replaced with laser welded gear assemblies identified by the presence of the letter"Z" or the letters "XO" on the retaining ring end of the gear axle or the letter "L", stamped on the distributor gear electrode. c. 1. Remove the distributor block from the magneto and the gears from the block. 2. (A). Inspect distributor gears and block for the presence of bronze colored particles and for indications of metal to metal contact of electrodes. (B). Inspect rotating electrode for looseness by holding the gear in one hand while attempting to move the distributor gear electrode relative to the axle, clock-wise and vertically. Any looseness of the rotating electrode is reason for rejection of distributor gear. 3. If the distributor block is contaminated with brass filings or bronze colored dust, inspect the engine as follows: (A). Observe engine pistons through spark plug hole for evidence of burning. (B). Check valve dry tappet clearance per engine manufacturer's instructions. If piston damage or lower than specified dry tappet clearance is present, the engine must be inspected, in accordance with the engine manufacturer's instructions, for continued airworthiness. 4. Reinstall serviceable distributor gears into a clean serviceable distributor block. Reassemble the magneto and check timing as appropriate. 5. (A). Make an engine log entry of compliance, including magneto serial number. (B). When the laser beam welded distributor gear has been installed in a D-3000 or D-3200 series magneto, identify that magneto by metal stamping the letter "X", on the upper left area of magneto data plate and make the appropriate log entry. Equivalent inspections and procedures must be approved by the Chief of the Engineering and Manufacturing Branch, AEA-210, Federal Aviation Administration (FAA) Eastern Region. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this AD can be accomplished. (Bendix Service Bulletins 618 and 619 pertain to paragraphs a and b respectively.) This Airworthiness Directive is effective November 12, 1981, and paragraph a. was effective upon receipt for all recipients of airmail letter dated June 5, 1981, which covered that subject.
2021-04-08: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS350B3 helicopters. This AD requires modifying the electrical system of the throttle twist grip, inspecting the routing of a microswitch electrical harness, and correcting the electrical harness routing if it is incorrect. This AD was prompted by reports of the engine remaining in idle when the twist grip was turned from the ''forced idle'' position to the ''flight'' position. The actions of this AD are intended to address an unsafe condition on these products.
2010-14-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: It has been evidenced by test that the tightening torque settings on the Rolls-Royce Trent 500 and Trent 700 forward (FWD) and aft (AFT) engine mount link pin retention bolts have always been higher than the design value. These bolts retain the washers that maintain the engine mount vertical load pins in position. If bolts, as a consequence of the over-torque, fail and move away, it would lead to loss of the vertical load pins, which could result in loss of the primary and/or secondary load path of the forward and/or aft engine mount which could potentially lead to engine separation. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
99-03-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model MD-11 series airplanes. This action requires a one-time inspection to detect discrepancies of certain wiring and insulation in the cockpit and cabin, and repair, if necessary. This amendment is prompted by test results obtained in support of an accident investigation. The actions specified in this AD are intended to prevent electrical arcing of certain wiring, which could cause a fire and/or smoke in the cockpit or cabin.
97-19-07: 97-19-07 DASSAULT AVIATION: Amendment 39-10127. Docket 97-NM-182-AD. Applicability: All Model Falcon 2000 series airplanes, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent an engineflame-out during a rapid throttle reduction, accomplish the following: (a) Within 7 days after the effective date of this AD, revise the Limitations and Abnormal Procedures Sections of the FAA-approved Airplane Flight Manual (AFM), in accordance with Dassault Service Bulletin F2000-80 (F2000-283), dated December 11, 1996. NOTE 2: This may be accomplished by inserting a copy of Temporary Change No. 34 (undated) to the Falcon 2000 AFM into the AFM. When this temporary revision has been incorporated in the general revisions of the AFM, the general revisions may be inserted in the AFM, provided the information contained in the general revisions is identical to that specified in Temporary Change No. 34. (b) Within 30 days after the effective date of this AD, install new placards stipulating the types of airplane fuel to be used, in accordance with Dassault Aviation Service Bulletin F2000-80 (F2000- 28-3), dated December 11, 1996. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The actions shall be done in accordance with Dassault Service Bulletin F2000-80 (F2000- 28-3), dated December 11, 1996. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, New Jersey. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. NOTE 4: The subject of this AD is addressed in French airworthiness directive 96-290-001(B), dated December 4, 1996. (f) This amendment becomes effective on September 29, 1997.
2022-11-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, EC130B4, and EC130T2 helicopters. This AD was prompted by the identification of certain parts needing maintenance actions, including life limits and maintenance tasks. This AD requires incorporating into maintenance records requirements (airworthiness limitations), 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.
2013-14-09: We are superseding airworthiness directive (AD) 2012-14-04 for certain Bombardier, Inc. Model DHC-8-100, -200, and -300 series airplanes. AD 2012-14-04 required replacing certain parking brake accumulators. This new AD retains this requirement. This new AD also requires installing restraint devices around the parking brake accumulator end caps. We are issuing this AD to prevent failure of a parking brake accumulator screw cap or end cap resulting in loss of the number 2 hydraulic system and damage to airplane structures, which could adversely affect the controllability of the airplane.
99-02-13: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France (Eurocopter) Model AS332C, L, and L1 helicopters, that requires the replacement of certain main rotor hub spindles (spindles) and flapping hinge pins (pins). This amendment is prompted by testing of aged frequency adapters, which shows that premature failure of the spindles and pins can occur due to increased loading from increased stiffness of the aged frequency adapters. The actions specified by this AD are intended to prevent the loss of a main rotor blade and subsequent loss of control of the helicopter.
89-12-06: 89-12-06 BRITISH AEROSPACE: Amendment 39-6226. Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent structural failure of the fuselage accomplish the following: A. Prior to the accumulation of 30,000 landings or within 1,600 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,600 landings, perform visual inspections of the fuselage frame splice joint, skin, stringers, and connecting structure at fuselage station 178 between stringers 2 left and 2 right in accordance with British Aerospace Alert Service Bulletin 53-A-PM5964, Issue 2, dated June 1, 1988. Any cracks found must be repaired prior to further flight, in accordance with the service bulletin. B. If cracks are found during inspections required by paragraph A., perform additional inspections in accordance with paragraph 2.2. of the Accomplishment Instructions, of British Aerospace Alert Service Bulletin 53-A-PM5964, Issue 2, dated June 1, 1988, and repair all cracks, prior to further flight, in accordance with the service bulletin. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Inc., Service Bulletin Librarian, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6226, AD 89-12-06) becomes effective on July 3, 1989.
93-08-09: 93-08-09 FAIRCHILD AIRCRAFT: Amendment 39-8556. Docket No. 93-CE-28-AD. Applicability: Models SA227-TT, SA227-AT, SA227-AC, and SA227-BC, airplanes (all serial numbers), certificated in any category that have the nose wheel steering system modified in accordance with Fairchild Service Bulletin (SB) 227-32-030, Issued: February 22, 1991, Revised: October 5, 1991; and Model SA227-DC airplanes (serial numbers 784 and 790 through 825), certificated in any category. Compliance: Required within the next 25 hours time-in-service, unless already accomplished. To prevent loss of directional control of the airplane during takeoff or landing caused by nose wheel steering malfunctions, accomplish the following: (a) For the Models SA227-TT, SA227-AT, SA227-AC, and SA227-BC airplanes, place a copy of this AD into the Limitations Section of the Airplane Flight Manual (AFM) in order to incorporate the following nose wheel steering system limitations: (1) Check the nose wheel steering prior to each takeoff using the procedures in the Normal Procedures section of the airplane flight manual. (2) The use of nose wheel steering for takeoff and landing is prohibited. Prior to each takeoff, turn the nose wheel arm switch to "OFF", and do not turn to "ON" until after landing and the airplane has slowed to taxi speed. (b) For the Model SA227-DC airplanes, incorporate FAA-Approved Model SA227-DC AFM Revision 8, dated April 2, 1993, into the Limitations Section of the AFM. This AFM revision specifies nose wheel steering limitations. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, FAA, Fort Worth, Texas 76193-0150. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth Airplane Certification Office. (e) All persons affected by this directive may obtain a copy of the document referenced from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490; or may examine information related to this AD at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (f) This amendment becomes effective on May 14, 1993.
62-16-02: 62-16-02 DOUGLAS: Amdt. 462 Part 507 Federal Register July 12, 1962. Applies to All Model DC-8 Aircraft With Outboard Flap Actuating Cylinder Douglas P/N 3643686. These Cylinders Can Be Identified As Having An Outside Diameter of 3.810-3.820 Inches At The Forward End Of The Barrel Where The Cylinders Attach To The Wing Flap Crank. \n\n\tCompliance required as indicated. \n\n\t(a) On aircraft incorporating flap quadrant stops which limit flap extension to 40 degrees full down, conduct a close visual inspection daily of the forward 1/4 inch of length and around the entire periphery of both outboard wing flap actuating cylinder barrels for evidence of cracks or fluid leakage. Conduct inspection with hydraulic pressure on. Investigate hydraulic fluid leakage to determine cause. Barrels showing evidence of cracks shall be replaced prior to further flight. \n\n\t(b) On aircraft not incorporating 40 degrees full-down quadrant stops, prior to each flight inspect in accordance with (a) until aircraft are modified as follows: \n\n\t\t(1) Install a stop on the control pedestal assembly as described on Serial E.0.001 to Douglas Drawing 5640901 which restricts flap extension to 46-48 degrees down travel or, install a new flap position quadrant, flap-detent locating nameplate and flap position placard in accordance with Figure (2) of Douglas DC-8 Service Bulletin No. 27-134 or FAA approved equivalent. \n\n\t\t(2) Rig the flap in accordance with the instructions contained in Addendum No. 1 dated June 12, 1962, to Douglas Alert Bulletin A27-134 or rig the flap in accordance with (d)(3). \n\n\t(c) When modifications in accordance with (b) have been accomplished, the preflight inspection required by (b) may be conducted daily. \n\n\t(d) The daily or preflight inspections required in (a), (b) and (c) may be discontinued if the following is accomplished: \n\n\t\t(1) Conduct initial inspection of both outboard barrel assemblies, P/N 3643686-1, in accordance with steps (1) through (4)of Figure (1) in DC-8 Service Bulletin No. 27-134. Barrels meeting the inspection requirements specified therein, may be continued in service. After this initial inspection, periodically reinspect barrels for cracks in accordance with step (1), mentioned above, at intervals not to exceed 2,500 hours' time in service thereafter. Barrels showing evidence of cracks shall be replaced prior to further flight. \n\n\t\t(2) Accomplish rework outlined in paragraph (b) (1). \n\n\t\t(3) Adjust all flap actuating cylinders and rig the flaps to the pertinent dimensions, flap travel limits and flap travel times specified in paragraph 2, Accomplishment Instructions, Kit C or D, paragraph E of Douglas DC-8 Service Bulletin No. 27-134, or an FAA approved equivalent. \n\n\t(e) The magnetic inspection, step (1), specified in (d)(1), may be discontinued: \n\n\t\t(1) After the fourth such inspection if the barrels, P/N 3643686-1, meet the inspection requirements of (d)(1), are shot peened in accordance with Figure (1) of Douglas DC-8 Service Bulletin No. 27-134, reidentified as P/N 3643686-501, and further identified with a color code or FAA approved equivalent; or \n\n\t\t(2) Upon installation of new shot peened barrels, P/N's 3643686-501 or 3774061-501. \n\n\t(f) Upon request of the operator an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the repetitive inspection intervals specified 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 such operator. \n\n\t(Douglas DC-8 Service Bulletin No. 27-134 dated July 20, 1962, covers this same subject.) \n\n\tThis directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegrams dated June 7, 1962, and June 14, 1962. \n\n\tRevised November 3, 1962.
2022-09-08: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by reports of a missing shim at a joint common to the main torque box (MTB) skin panel and rear spar root fitting. This AD requires inspecting the MTB skin panel and rear spar root fitting for cracking and delamination, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.