Results
97-01-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Textron Lycoming reciprocating engines. This action requires removal from service of defective piston pins, and replacement with serviceable parts. This amendment is prompted by a report of failure of a piston pin. The actions specified in this AD are intended to prevent piston pin failure, which could result in engine failure.
2004-23-01: The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes with any Lear Romec RR53710B type or Lear Romec RR53710K fuel booster pump (Pilatus part number 968.84.11.401; 968.84.11.403; or 968.84.11.404) installed. This AD requires you to check the airplane logbook to determine whether any installed fuel booster pump has been modified with spiral wrap to protect the wire leads and has the suffix letter "B" added to the serial number of the fuel booster pump identification plate. If any installed fuel booster pump has not been modified, you are required to inspect any installed fuel booster pump wire lead for defects; if defects are found, replace the fuel booster pump with a modified fuel booster pump with spiral wrap that protects the wire leads; or if no defects are found, install spiral wrap to protect any wire leads and add the suffix letter "B" to the serial number of the fuel booster pump identification plate. The pilot is allowed to do the logbook check. If the pilot can positively determine that the fuel booster pump wire leads with spiral wrap are installed following the service information and that the suffix letter "B" is included in the serial number of the fuel booster pump identification plate, no further action is required. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct any defects in the leads of any fuel booster pump, which could result in electrical arcing. This failure could lead to a fire or explosion in the fuel tank.
85-19-06: 85-19-06 BURKHART GROB: Amendment 39-5131. Applies to model G102 Astir CS Gliders (serial numbers 1001 through 1536 inclusive) certificated in any category. Compliance is required as indicated unless already accomplished. To Prevent failure of the air brake locking levers, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD cut inspection holes in the wing root ribs and inspect the air brake levers (P/Ns 102-4123 and 102- 4124) in accordance with Instruction 1 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985. (b) If solid cast aluminum levers are found, accomplish paragraph (d). (c) If cast aluminum levers with a centerhole are found, accomplish the following: (1) Install inspection windows in the wing and replace page 3 and add page 26a to the flight manual in accordance with Instruction 2 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985, no later than March 31, 1986. (2) Within the next 10 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 10 hours, inspect the airbrake locking levers for cracks in accordance with Instruction 3 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985, until accomplishment of Instruction 4 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985. If cracks are found, replace airbrake locking lever with a serviceable part before further flight. (d) Replace the cast aluminum airbrake levers with the sheet aluminum airbrake levers in accordance with Instruction 4 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985, no later than 3000 hours time in service. NOTE: Dimensions shown in TM 306-26 are in millimeters. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium 09667-1011, telephone 513.38.30. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office may adjust the compliance time specified in this AD. Grob-Werke GmbH Technical Information TM 306-26 dated March 25, 1985, is 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 this document from the manufacturer may obtain copies upon request to Burkhart Grob of America Incorporated, 1070 Navajo Drive, Bluffton Airport Complex, Bluffton, Ohio 45817. These documents also may be examined at the Office of the Regional Counsel, FAA, New England Region, Room 311, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on September 19, 1985.
2023-04-16: The FAA is superseding Airworthiness Directive (AD) 2020-21- 20, which applied to certain Dassault Aviation Model FALCON 900EX airplanes. AD 2020-21-20 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and/or airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2020-21-20 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations; as specified in 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.
2004-25-05: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200C, 747-200F, 747-300, 747SP, and 747SR series airplanes. This AD requires repetitive inspections to detect cracks and fractures of the strut front spar chord assembly at each strut location, and repair if necessary. This AD is prompted by a report of a fractured front spar chord assembly for strut No. 3, which resulted in the loss of the strut upper link load path. We are issuing this AD to prevent loss of the strut upper link load path and consequent fracture of the diagonal brace, which could result in in-flight separation of the strut and engine from the airplane.
81-14-02: 81-14-02 MAULE AIRCRAFT CORPORATION: Amendment 39-4146. Applies to M-4 and to M-5 series airplanes certificated in all categories. M-4 Series. M-4, S/N 4 through 94, 1001 through 1045, 1S through 3S, 1T through 3T, 1C through 11C; M-4-210C, S/N 1001C through 1117C; M-4-220S, S/N 2001S; M-4-220C, S/N 2001C through 2190C; M-4-180C, S/N 3001C through 3006C. M-5 Series. M-5-220C, S/N 5001C through 5057C; M-5-210C, S/N 6001C through 6204C; M-5-235C, S/N 7001C through 7254C; M-5-180C, S/N 8001C and M-5-210TC, S/N 9001C. Compliance is required as indicated, unless already accomplished. To prevent failure of the rudder pedal V-bar and associated structure of the rudder bar, within 25 hours time in service after the effective date of this AD accomplish the following: (a) Visually inspect the rudder pedal V-bar tube for cracks with at least a 10-power magnifying glass. NOTE: Instructions for access to the rudder bar are outlined in Maule Aircraft Corporation Service Bulletin No. 2, dated 2/17/81. (b) If no cracks are found, modify the rudder bar assembly in accordance with the Maule Service Bulletin #2, dated 2/17/81. (c) If a crack is found, prior to further flight accomplish either 1 or 2 below, as appropriate: 1. If the crack is one inch or less in length, install modified rudder bar, P/N 4130F-12, in accordance with the instructions contained in Maule Service Bulletin #2, dated 2/17/81, or stop drill at the end of the crack, weld and reinforce in accordance with the instructions provided in the Maule Service Bulletin #2, dated 2/17/81, and Advisory Circular 43.13-1A, Chapter 2, Aircraft Metal Structure, Section 2, Welding. 2. If the crack exceeds one inch in length, install modified rudder bar, P/N 4130F-12, in accordance with the instructions contained in Maule Service Bulletin #2, dated 2/17/81. (d) Make appropriate maintenance record entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. This amendment becomes effective July 1, 1981.
2014-08-11: We are superseding Airworthiness Directive (AD) 2009-24-07 for certain the Boeing Company Model 737-600, -700, -700C, and -800 series airplanes. AD 2009-24-07 required repetitive lubrications of the right and left main landing gear (MLG) forward trunnion pins. AD 2009-24-07 also required an inspection for discrepancies of the transition radius of the MLG forward trunnion pins, and corrective actions if necessary. For certain airplanes, AD 2009-24-07 required repetitive detailed inspections for discrepancies (including finish damage, corrosion, pitting, and base metal scratches) of the transition radius of the left and right MLG trunnion pins, and corrective action if necessary. Replacing or overhauling the trunnion pins terminates the actions required by AD 2009-24-07. This new AD adds airplanes to the applicability of AD 2009-24-07. This AD was prompted by reports of corrosion protection damage to the forward trunnion pin on additional airplanes. We are issuing this AD to prevent stress corrosion cracking of the forward trunnion pins, which could result in fracture of the pins and consequent collapse of the MLG.
2023-04-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive 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.
81-17-03: 81-17-03 HILLER AIRCRAFT: Amendment 39-4187. Applies to Model UH-12 all series helicopters, certified in all categories, including Soloy Conversions STCs SH177WE and SH178WE, equipped with Main Transmission P/Ns 23500-3 and 23700-3, -5, -7 or -9. Compliance required as indicated, unless already accomplished. To prevent failure of the main transmission, accomplish the following: (a) Within 25 hours' additional time in service from the effective date of this AD, inspect the main transmission oil filter and chip detector according to paragraph 2 of Hiller Service Notice No. 23-2, dated 28 July 1981. (1) If magnetic chips or a quantity of gold colored flecks are present in the filter bowl, open transmission, inspect planetary system and replace worn parts per Hiller Overhaul Manual, before further flight. (2) If no chips are present on the magnetic chip detector, and only a trace of gold flecks is found in the filter bowl, clean filter and bowl, replace andmake detailed log book entry of the condition. If gold flecks are found after an additional 25 hours' time in service during an inspection per (a) above, replace with like serviceable part(s) per (a)(1), above, before further flight. (b) After completion of (a) (1) or (2) above, inspect, every 25 hours' time in service for turboshaft powered aircraft and 50 hours' time in service for reciprocating engine powered aircraft, according to (a) above. (c) Prior to 1200 hours' time in service or within the next 100 hours, after the effective date of this AD, remove P/N 23586-3 spacers from service and replace with serviceable parts. (d) 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. (e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineeringand Manufacturing Branch, FAA Western Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made apart hereof pursuant to 5 U.S.C. 552(a(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Hiller Aviation, 2075 W. Scranton Avenue, Porterville, California 93257. These documents may also be examined at 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 August 24, 1981.
96-26-07: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737 series airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to include procedures that will enable the flight crew to take appropriate action to maintain control of the airplane during an uncommanded yaw or roll condition, and to correct a jammed or restricted flight control condition. This amendment is prompted by an FAA determination that such procedures currently are not defined adequately in the AFM for these airplanes. The actions specified in this AD are intended to ensure that the flight crew is advised of the potential hazard associated with a jammed or restricted flight control condition and of the procedures necessary to address it.