Results
2006-03-08: The FAA adopts a new airworthiness directive (AD) for all airplanes equipped with Aero Advantage ADV200 series (part numbers ADV211CC and ADV212CW) vacuum pumps installed under supplemental type certificate number SA10126SC, through field approval, or other methods. This AD requires you to remove from service any affected vacuum pump and install an FAA-approved vacuum pump other than the affected part numbers. This AD results from several reports of pump chamber failure. We are issuing this AD to prevent vacuum pump failure or malfunction during instrument flight rules (IFR) flight that could lead to loss of flight instruments critical for flight. The loss of flight instruments could cause pilot disorientation and loss of control of the aircraft.
99-08-12: This amendment adopts a new airworthiness directive (AD), that requires revisions to the Engine Time Limits section in the Engine Manual (EM) for Pratt & Whitney (PW) JT9D series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts which indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, that if allowed to continue in service, could result in uncontained failures. The actions specified by this proposed AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
99-08-13: This amendment adopts a new airworthiness directive (AD), that requires revisions to the Life Limits Section of the manufacturer's Instructions for Continued Airworthiness (ICA) for General Electric Company (GE) CF6-80A, CF6-80C2 and CF6-80E1 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD also requires that an air carrier's approved continuous airworthiness maintenance program incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
89-10-07: 89-10-07 PRATT & WHITNEY: Amendment 39-6181. Applicability: Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7AH, -7H, -7F, -7J, and -20 turbofan engines. Compliance: Required as indicated, unless already accomplished. To prevent a diffuser case Number 4 or Number 7 strut failure that can cause a Number 3 bearing compartment fire and subsequent nacelle fire, accomplish the following: (a) Install strut insert assembly Part Number 804698-01 into both the Number 4 and Number 7 diffuser case struts, in accordance with the Accomplishment Instructions of PW Service Bulletin (SB) 5730, dated February 4, 1987, at the next engine shop visit after the effective date of this AD, but not later than August 31, 1991. NOTE: For the purpose of this AD, engine shop visit is defined as maintenance entailing a separation of the high pressure compressor case and diffuser case "K" flange. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 toa base where the AD may be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternative method of compliance with the requirements of this AD or adjustment 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, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. The diffuser case strut insert incorporation shall be done in accordance with PW SB 5730, dated February 4, 1987. 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 Pratt & Whitney, Publication Department, P.O. Box 611, Middletown, Connecticut 06457. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal AviationAdministration, 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. This amendment (39-6181, AD 89-10-07) becomes effective on May 30, 1989.
2006-02-51: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company Model 390 airplanes. This AD contains the same information as emergency AD 2006-02-51 and publishes the action in the Federal Register. This AD requires you to visually inspect the hydraulic tube assembly (P/N 390-580035-0001 or P/N 390- 580035-0005) and the clamp (P/N MS21919WCJ6 or P/N MS21919WCJ7) (or FAA-approved equivalent part numbers), as specified in the service information; replace the clamp at each inspection; replace the hydraulic tube assembly immediately if any of the problems identified in the service bulletin are found; and report the results of each inspection or replacement to the FAA. This AD results from failure of the hydraulic tube assembly, which caused in-flight loss of hydraulic fluid. We are issuing this AD to prevent failure of the hydraulic tube assembly and consequent leaking of hydraulic fluid. This failure could result in loss of hydraulic system functionsand risk of fire because of flammable fluid leakage in the engine nacelle and lead to loss of control of the airplane.
99-08-10: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-100, -200, -300, -SP, and -400F series airplanes. Among other things, this amendment requires repetitive leak tests of the lavatory drain system and repair, if necessary; installation of a cap or flush/fill line ball valve on the flush/fill line; periodic seal changes; and replacement of any "donut" type valves installed in the waste drain system. This amendment is prompted by continuing reports of damage to airframes and damage to property on the ground, caused by "blue ice" that forms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from the airplane fuselage. The actions specified by this AD are intended to prevent damage to airframes and property on the ground that is associated with the problems of "blue ice" that forms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from theairplane fuselage.
99-08-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and -320 series airplanes, that currently requires a one-time inspection of the main landing gear (MLG) actuator fitting bolt holes for correct alignment, and rework of the fitting surface and bolt replacement, if necessary. This amendment requires replacement of the MLG actuator fitting bolts with new, improved bolts. This amendment also revises the applicability of the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the MLG actuator fitting bolts, which could result in the inability to retract the MLG and attain an adequate climb gradient.
79-25-03: 79-25-03 DETROIT DIESEL ALLISON: Amendment 39-3625. Applies to Model 501-D13, 501-D13A, 501-D13D, 501-D13E, and 501-D13H engines equipped with second, third, and fourth stage turbine wheels P/N's 6829072, 6847112, 6788833, 6842143, 6841223, 6846553, 6738424, and 6843014. Compliance required as follows unless previously accomplished: (a) For second stage turbine wheels, remove from service in accordance with FAA approved revision of 501-D13 CSL-235 dated December 13, 1979. (b) For third and fourth stage turbine wheels, remove from service in accordance with FAA approved revision of 501-D13 CSL-253 dated December 13, 1979. Detroit Diesel Allison Commercial Service Letters 501-D13 CSL-235, 501-D13 CSL-253, and Commercial Overhaul Information Letter 501-D13 COIL-349 revised as of December 13, 1979 are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). The incorporated service documents may be obtained from Detroit Diesel Allison, Division ofGeneral Motors Corporation, Indianapolis, Indiana 46206. This amendment becomes effective on December 13, 1979.
64-04-05: 64-04-05 NAVION: Amdt. 684 Part 507 Federal Register February 11, 1964. Applies to All Navion D, E, F, and G Aircraft, Serial Numbers NAV-4-2 and up. Compliance required within 10 hours' time in service after the effective date of this AD and thereafter within every 100 hours'-time in service. (a) Visually inspect wing panel outboard of Wing Stations 130 (outboard edge of flap) for loose rivets. Replace loose rivets with the next larger size. Where this is impractical due to edge distance, interference, etc., install a protruding head rivet of the same diameter located between the loose rivet and the next adjacent rivet. (b) Install 4 AD 4 protruding head rivets both top and bottom skin equally spaced between the last 5 rivets in stringer No. 3. This is at the front tip tank attachment. (c) This inspection is no longer necessary if the skin with flush rivets is replaced with new skin of equivalent strength and protruding head rivets of the original size are used. Other modifications must be approved by a Regional FAA Engineering and Manufacturing Branch. (Navion Service Letter No. 85 covers this same subject.) This directive effective February 17, 1964.
2006-02-11: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires doing repetitive detailed inspections for accumulation of debris (blockage) in the drain holes of the pitot tubes, and cleaning the hole if any evidence of debris is found. This AD results from reports of blocked drain holes of the pitot tubes. We are issuing this AD to prevent blocked drain holes of the pitot tubes, which could result in the accumulation of water in the pitot-static system and consequent failure of that system. Failure of the pitot-static system could result in erroneous airspeed indications in the cockpit and consequent loss of airspeed control.