2020-03-17: The FAA superseding Airworthiness Directive (AD) 2015-24-04, which applied to certain Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. AD 2015-24-04 required repetitive inspections of the cage assembly for damaged or detached window louver panel assemblies (WLPAs) and blowout panels (BOPs), and corrective actions if necessary. This AD requires one-time inspections of the WLPAs and BOPs, corrective actions if necessary, and a revision of the existing maintenance or inspection program, as applicable, to incorporate new airworthiness limitations, which would terminate the inspection requirement. This AD was prompted by a determination that new airworthiness limitations, as well as additional actions, are necessary toaddress the unsafe condition. The FAA is issuing this AD to address the unsafe condition on these products.
|
78-05-05: 78-05-05 PIPER AIRCRAFT CORPORATION: Amendment 39-3148. Applies to PA-31 and PA-31-325 and PA-31-300 aircraft, S/N 31-2 through 31-7512029, and PA-31-350 aircraft, S/N 31-5001 through 31-7552052 certificated in all categories, except airplanes modified to incorporate all three kits denoted in Piper Aircraft Corporation Service Letter 739, dated June 2, 1975.
Compliance required within the next 50 hours in service after the effective date of this AD, unless already accomplished.
To assure proper latching and thereby prevent inadvertent opening of the cabin door in flight, accomplish the modification excepting the compliance time paragraph described in Piper Aircraft Corporation Service Letter No. 803A, dated November 3, 1977, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
Upon request, with substantiating data, submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
This amendment is effective March 8, 1978.
|
2006-11-05R2: The FAA is revising an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-22B series, RB211-524B, -524C2, -524D4, -524G2, -524G3, and -524H series, and RB211-535C and -535E series turbofan engines with high pressure compressor (HPC) stage 3 disc assemblies, part numbers (P/Ns) LK46210, LK58278, LK67634, LK76036, UL11706, UL15358, UL22577, UL22578, and UL24738 installed. That AD currently requires removing from service certain disc assemblies before they reach their full published life if not modified with anticorrosion protection. This AD requires the same actions but relaxes the removal compliance time for certain disc assemblies that have a record of detailed inspection. This AD results from the FAA allowing certain affected disc assemblies that have a record of a detailed inspection, to remain in service for a longer period than the previous AD allowed. We are issuing this AD to relax the compliance time for disc assemblies manufactured both ``before and after 1990'' by providing an option to track the disc life based on a record of a detailed inspection rather than by its entry into service date, while continuing to prevent corrosion-induced uncontained disc assembly failure, resulting in damage to the airplane.
DATES: Effective February 21, 2008. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of February 24, 2004 (69 FR 2661, January 20, 2004).
We must receive any comments on this AD by April 7, 2008.
|
93-14-04: 93-14-04 AIRBUS INDUSTRIE: Amendment 39-8628. Docket 92-NM-216-AD.
Applicability: Model A320 series airplanes; manufacturer's serial numbers 002 through 008, inclusive, 010 through 078, inclusive, and 080 through 107, inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced structural integrity of the fuselage, accomplish the following:
(a) Prior to the accumulation of 12,000 total landings, or 6 months after the effective date of this AD, whichever occurs later, accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD, in accordance with Airbus Industrie Service Bulletin A320-53-1024, dated September 23, 1992:
(1) Conduct an eddy current inspection to detect cracking around the fastener bolt holes at the inboard flange of the floor beam, in the side box-beams, at the two sides of the pressure floor, and at the vertical integral stiffener between frame 42 and frame 43; and
(2) Conduct a detailed visual inspection to detect cracking of the fillet radius of the top outboard flange and the flange corner-radius of the slanted inboard flange of the side box-beam between frame 42 and frame 43.
(b) If no crack is detected during either inspection required by paragraph (a) of this AD, repeat the inspections at intervals not to exceed 6,000 landings.
(c) If a crack is detected during the inspections required by paragraph (a) or (b) of this AD, prior to further flight, repair the crack in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(d) Prior to the accumulation of 18,000 total landings, accomplish Modification 21202, in accordance with Airbus Industrie Service Bulletin A320-53-1023, dated September 23, 1992, as amended by Service Bulletin Change Notice 0A, dated January 20, 1993; or Revision 1, dated March 23, 1993. Accomplishment of this modification constitutes terminating action for the inspection requirements of this AD.
(e) 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.
(f) 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.
(g) The inspections shall be done in accordance with Airbus Industrie Service Bulletin A320-53-1024, dated September 23, 1992. The modification shall be done in accordance with Airbus Industrie Service Bulletin A320-53-1023, dated September 23, 1992, which includes Appendix 1, dated September 23, 1992; Service Bulletin Change Notice 0A, dated January 20, 1993, for Airbus Industrie Service Bulletin A320-53-1023, dated September 23, 1992; or Airbus Industrie Service Bulletin A320-53-1023, Revision 1, dated March 23, 1993, which includes Appendix 1, dated September 23, 1992. 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(h) This amendment becomes effective on August 23, 1993.
|
99-04-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that requires removal of the fuel level sensing amplifier (FLSA) of the trim tank system, modification of the polarization pin code in the electronics bay, and installation of a new, improved FLSA. 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 continuous aft transfer of fuel due to the FLSA not supplying electrical power to the trim tank overflow sensor, which could result in potential loss of fuel during flight.
|
98-03-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to prohibit use of the autobrake during landing on contaminated runways. This action also requires replacement of the brake and steering control unit (BSCU) with a new BSCU, which eliminates the need for the AFM revision. For certain airplanes, this action also requires installation of new brakes. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent insufficient braking capability, which could increase the potential for landing overrun.
|
2020-03-14: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of loss of retention of the regulator inlet filter retainer on certain crew oxygen cylinder assemblies. This AD requires an inspection of the crew oxygen cylinder assembly for any discrepancy and replacement of an affected crew oxygen cylinder assembly with a serviceable part, 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.
|
83-07-08: 83-07-08 SHORT BROTHERS AND HARLAND, LTD.: Amendment 39-4606. Applies to Model SC-7, Series 3 (all serial numbers) airplanes certificated in any category.
Compliance: Required as indicated, unless already accomplished.
To preclude malfunction of the ground/air lever mechanism which may prevent the power lever from entering the Beta mode, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following:
(a) Modify the ground/air lever P/N SC-7-47-5254 in the engine control system in accordance with Shorts Service Bulletin No. 76-58, Revision 1, dated December 4, 1980.
(b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished.
(c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium.
This amendment supersedes AD 80-09-01, Amendment 39-3754.
This amendment becomes effective on April 11, 1983.
|
2008-17-11: 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 found that some "caution'' messages issued by the Flight Guidance Control System (FGCS) are not displayed on aircraft equipped with [certain] EPIC software load[s] * * *. Therefore, following a possible failure on one FGCS channel during a given flight, such a failure condition will remain undetected * * *. If another failure occurs on the second FGCS channel, the result may be a hardover command by the autopilot.
An unexpected hardover command may cause a sudden roll, pitch, or yaw movement, which could result in reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
|
2008-03-08: 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:
Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA has published Special Federal Aviation Regulation 88 (SFAR88) * * * [which] required * * * [conducting] a design review against explosion risks.
The unsafe condition is the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
|