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61-15-04: 61-15-04 LOCKHEED: Amdt. 309 Part 507 Federal Register July 21, 1961. Applies to All 188 Series Aircraft Incorporating A Lounge Using Hardman Seats. Compliance required as indicated. Reports have been received that grommets are missing in some of the aft lounge safety belt cable guide brackets. Grommets are required in these brackets to permit the cable to withstand the design load. Within the next 100 hours' time in service inspect the safety belt cable guide bracket, Hardman P/N 5072-1, of the left and right aft lounge seats for presence of nylon grommets. If the nylon grommets are missing, install nylon grommets, P/N 295957-10A (United Carr Fastener Corp.), or equivalent, or restrict occupancy of the left and right aft lounge seats during takeoff and landing until such time as grommets are installed. (Lockheed Service Bulletin 88/SB-541 refers to the same subject.) This directive effective August 2, 1961.
2003-17-05: This amendment adopts a new airworthiness directive (AD) that applies to all Short Brothers and Harland Ltd. (Shorts) Models SC-7 Series 2 and SC-7 Series 3 airplanes. This AD establishes a technical service life for these airplanes and allows you to incorporate modifications, inspections, and replacements of certain life limited items to extend the life limits of these airplanes. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of critical structure of the aircraft caused by fatigue.
2017-14-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of an aborted takeoff because the rudder pedals were not operating correctly. Investigation revealed a protruding screw in the rudder pedal heel rest adjacent to the pedals. This AD requires a torque check of the screws in the cover assembly of the heel rest for both the Captain and the First Officer's rudder pedals, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-14-11: We are superseding Airworthiness Directive (AD) 2007-13-08, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2007-13-08 required repetitive inspections of the auxiliary power unit (APU) starter motor, APU inlet plenum, and APU air intake for discrepancies; repetitive cleaning of the APU air intake; and applicable corrective actions. This AD expands the applicability of AD 2007-13-08, and includes an optional terminating installation for the repetitive actions. This AD was prompted by a determination that the unsafe condition could occur on additional airplanes. We are issuing this AD to address the unsafe condition on these products.
60-11-03: 60-11-03 LOCKHEED: Amdt. 159 Part 507 Federal Register May 24, 1960. Applies to All 188 Series Aircraft. Compliance required as indicated. Due to loose attachments and cracked quick engine change upper cowl panel longerons the following inspections are required. Prior to dispatch from a terminal where inspection facilities are available, unless already accomplished within the last 300 hours' time in service, and thereafter at every 300 hours' time in service, inspect the top cowl panel upper longerons and the attachments at the rear fittings for cracks or loose attachments. (a) Replace loose attachments in the longeron fittings. Acceptable replacements are: (1) One-sixty-fourths-inch diameter oversize Hi-Lok (P/N HL 56-6 pin, P/N HL 64-6-5 pin, P/N HL 85-6 collar). (2) Thirteen-sixty-fourths-inch diameter NAS type close tolerance screw, minimum heat treat 160,000 p.s.i. Ream to oversize hole limits of 0.212-0.2192-inch diameter. (3) Seven-thirty-seconds-inch diameter NAS type close tolerance screws; minimum heat treat 160,000 p.s.i.; minimum edge distance, 1 1/2 diameters. Ream to oversize hole limits of 0.2181-0.2192-inch diameter. (4) It is satisfactory to mix Huck bolts and Hi-Lok fasteners, but it is not acceptable to mix NAS type screws with Huck bolts or Hi-Lok fasteners. (b) Cracked longerons must be replaced or an FAA approved repair incorporated before next flight. The preceding inspections may be discontinued after the incorporation of the modifications contained in Lockheed Service Bulletin 88/SB-500. (Lockheed Alert Service Bulletin No. 467 covers this same subject.) This airworthiness directive sent by telegram to all operators of 188 aircraft on April 29, 1960. Revised September 29, 1960. Revised May 13, 1961.
2017-14-05: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA330J helicopters. This AD requires replacing certain hydraulic pumps and is prompted by reports of broken screws that attach the cover of the hydraulic pump. The actions of this AD are intended to prevent an unsafe condition on these products.
2017-13-12: We are adopting a new airworthiness directive (AD) for all Airbus Model A318 and A319 series airplanes; Model A320-211, -212, - 214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH), which indicates that the main landing gear (MLG) does not comply with certification specifications, which could result in a locking failure of the MLG side stay. This AD requires modification or replacement of certain MLG side stay assemblies. We are issuing this AD to address the unsafe condition on these products.
80-12-51 R2: 80-12-51 R2 PRATT & WHITNEY AIRCRAFT: Amendment 39-3809. Applies to all Pratt & Whitney Aircraft JT3D series turbofan engines. Compliance required as indicated. To prevent possible first stage fan blade failures resulting from low cycle fatigue, perform inspections in accordance with the schedule below: 1. Within 50 cycles after May 27, 1980, unless already accomplished, and every 200 cycles thereafter, perform a visual inspection of the critical area of the fan blade convex airfoil surface, in accordance with Pratt & Whitney Aircraft All Operator Telegram Nos. JT3D/72-00/PSE.WJM.0-5-26-1 and JT3D/72-00/PSE.WJM.0-5- 30-1. Remove from service any blade having a visual indication, crack, lap, or blend in the critical area. Any questionable visual indication may be dye penetrant inspected for verification. If the dye check is positive, remove from service. If there is no positive dye check indication, repeat within the next 50 cycles and every 50 cycles thereafter.2. Within 200 cycles after the effective date of this amendment, unless already accomplished, and every 2,200 cycles thereafter, perform an ultrasonic inspection of the fan blade in accordance with the provisions of Pratt & Whitney Alert Service Bulletin No. 5136, dated May 30, 1980, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. If any crack indications are found, the blade must be removed from service prior to further flight. 3. Once the ultrasonic inspections of Paragraph 2 have been initiated, the visual inspections per Paragraph 1 may be discontinued. Upon request of the operator, an equivalent method of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, New England Region, may adjustthe 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 that operator. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Pratt & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts, an at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 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 the New England Region. This amendment amends TAD No. T 80NE-26 issued May 28, 1980, as amended by TAD No. T 80-12-51 effective June 2, 1980. This Amendment 39-3809 becomes effective July 1, 1980.
2024-13-06: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a determination that certain left-hand (LH) and right-hand (RH) pylon bleed air leak detectors (BALDs) might be defective, due to incorrect manufacturing processes and incomplete acceptance test procedures. This AD requires a one-time operational check of affected parts and, depending on findings, accomplishment of applicable corrective action, and limits the installation of affected parts under certain conditions, 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.
79-08-01 R1: 79-08-01 R1 GATES LEAR JET: Amendment 39-3447 as amended by Amendment 39- 4361. Applies to Models 35, 35A, 36 and 36A airplanes equipped with Aeronca thrust reversers. COMPLIANCE: Required as indicated unless already accomplished. To preclude inadvertent thrust reverser deployment and possible loss of aircraft control, prior to next flight accomplish the following: A) Insert in the Aeronca Thrust Reverser Supplement to the Airplane Flight Manual the FAA-approved temporary changes shown herein as Figures I, II and III or the FAA-approved Flight Manual Supplement changes (temporary or permanent) supplied by the manufacturer and containing the same information as the above figures. B) Operate the airplane in accordance with instructions in the Flight Manual Supplement changes specified in Paragraph A) of this Airworthiness Directive. C) Airplanes may make one flight to the location where the changes to the Aeronca Thrust Reverser Supplement to the Airplane Flight Manual specified in this Airworthiness Directive are available, providing the Exterior Inspection in Figure II and Limitations in Figure I are complied with. D) The installation of Gates Learjet Thrust Reverser Blocker Door Position Indication System, per Gates Learjet Corporation Modification Kit No. AMK 81-6, constitutes terminating action for the requirements of paragraphs A), B), and C) of this AD. E) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-3447 became effective on April 19, 1979, to all persons except those to whom it had already been made effective by an airmail letter from the FAA dated March 1, 1979. This Amendment 39-4361 becomes effective April 19, 1982. FIGURE I TEMPORARY CHANGE, SUPPLEMENT FOR AERONCA THRUST REVERSERS Aircraft Affected: All Gates Lear Jet Model 35, 36, 35A, 36A Aircraft equipped with Aeronca Thrust Reversers. Description of Change: Add Limitations to Section I of the Aeronca Thrust Reverser AFM Supplement. Filing Instructions: Insert this page adjacent to page 2 of 23 in your Thrust Reverser Supplement and retain until further notice. Amend Section I - Limitations by adding the following limitations: Section I - LIMITATIONS (Cont) 7. Thrust Reversers must not be operated prior to takeoff. 8. Thrust Reversers must not be used to control taxi speed, except after landing. 9. Thrust Reversers must not be used for touch and go landings. 10. After Thrust Reversers have been deployed, a visual check of proper door stowing must be made prior to takeoff. 11. Operational Procedures in this Thrust Reverser Supplement are mandatory. FIGURE II TEMPORARY CHANGE, SUPPLEMENT FOR AERONCA THRUST REVERSERS Aircraft Affected: All Gates Lear Jet Model 35, 36, 35A, 36A Aircraft equipped with Aeronca Thrust Reversers. Description of Change: Add Thrust ReverserOperational Changes. Filing Instructions: Insert this page adjacent to page 2 of 23 in your Thrust Reverser Supplement and retain until further notice. Add the following EXTERIOR INSPECTION to Section II - NORMAL PROCEDURES EXTERIOR INSPECTION (Power-Off) A. Inspect both thrust reversers as follows: 1. Check that thrust reverser upper and lower blocker doors are completely stowed. Change BEFORE TAKEOFF to read as follows: CAUTION: Do not operationally check thrust reversers before takeoff. 1. Thrust Reverser Circuit Breaker - In. 2. Thrust Reverser Position Indicator Lights - Extinguished. 3. Deleted. NOTE: This Temporary Change deletes Thrust Reverser Operational Check, Before Takeoff. FIGURE III TEMPORARY CHANGE, SUPPLEMENT FOR AERONCA THRUST REVERSERS Aircraft Affected: All Gates Lear Jet Model 35, 36, 35A, 36A Aircraft with Aeronca Thrust Reversers. Description of Change: Add Postflight Operational Check. Filing Instructions: Insert this page adjacent to page 4 of 23 in your Thrust Reverser Supplement and retain until further notice. Add the following POSTFLIGHT Operational Check after NORMAL PROCEDURES - After Landing: POSTFLIGHT A. Operationally check Thrust Reverser as follows: CAUTION: It is recommended that the aircraft be headed into the wind during static thrust reverser ground operational check. Keep thrust reverser deployed time to a minimum to prevent possible engine reingestion of exhaust gases. a NORM-EMER STOW Switch - NORM, EMER STOW light extinguished. b Thrust Levers - IDLE. c Thrust Reverser Levers - Pull to deploy lever stop position. UNLOCK lights will come on and then go off when DEPLOY lights come on. Check that the throttle lock releases when the DEPLOY lights illuminate. d NORM-EMER STOW Switch - EMER STOW, EMER STOW light illuminated. DEPLOY lights will go off when UNLOCK lights go on. UNLOCK lights will go off when system is stowed. eThrust Reverser Levers - Push to stow position. f NORM-EMER STOW Switch - NORM, EMER-STOW lights extinguished. g Thrust Reverser Levers - Pull to deploy position. Check for proper light sequence. h Thrust Reverser Levers - Push to stow position. Check for proper light sequence.