Federal Aviation Administration 2006 – Federal Register Recent Federal Regulation Documents

The Federal Aviation Administration (FAA) is requesting public comment on a proposal to decommission all 54 Direction Finders (DF) and the associated DF approaches in all states other than Alaska. DF's have been used sparingly over the last nine years and the equipment is beyond its useful lifecycle. Improved radar coverage, pilot education and technologies such as area navigation (RNAV) and global positioning satellite (GPS) have reduced the utilization of DF steers and have essentially made DF's obsolete. A Federal Safety Risk Management Panel (SRMP) has determined that if pilots need orientation assistance, that our existing orientation methods, VOR, ADF, and GPS are reliable and meet the needs of our aviation community. Decommissioning would coincide with the Flight Services service provider's plan to consolidate the 58 flight service stations to 20 facilities.

This document proposes to modify Class E airspace at Chamberlain, SD. Standard Instrument Approach Procedures have been developed for Chamberlain Municipal Airport, Chamberlain, SD. Controlled airspace extending upward from 700 feet or more above the surface of the earth is needed to contain aircraft executing these approaches. This action would increase the area of the existing controlled airspace for Chamberlain, SD.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200 series airplanes. This AD requires a one- time deactivation of the auxiliary fuel system, repetitive venting and draining of the auxiliary fuel tank sumps, and revising the Limitations section of the airplane flight manual to limit the maximum cargo weight. This AD results from a re-evaluation of the floor structure and cargo barriers conducted by the STC holder. We are issuing this AD to prevent structural overload of the auxiliary fuel tank support structure, which could cause the floor beams to fail, damaging the primary flight controls and the auxiliary power unit fuel lines that pass through the floor beams, resulting in loss of control of the airplane. We are also issuing this AD to prevent structural overload of the cargo barriers, which could cause the barriers to fail, allowing the cargo to shift, resulting in damage to the auxiliary fuel tanks, residual fuel leakage, and consequent increased risk of a fire.

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires repetitive detailed and eddy current inspections of the main fittings of the main landing gears (MLG) to detect discrepancies, and related investigative/corrective actions if necessary. The existing AD also requires servicing the shock strut of the MLGs; inspecting the shock strut of the MLGs for nitrogen pressure, visible chrome dimension, and oil leakage; and servicing any discrepant strut. This proposed AD would require installing a new, improved MLG main fitting, which would terminate the repetitive inspection and servicing requirements of the existing AD. This proposed AD results from stress analyses that showed certain main fittings of the MLGs are susceptible to premature cracking, starting in the radius of the upper lug. We are proposing this AD to detect and correct premature cracking of the main fittings of the MLGs, which could result in failure of the fittings and consequent collapse of the MLGs during landing.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 727 airplanes. This AD requires repetitive measurements of the freeplay of the left and right outboard aileron balance tabs and of the upper and lower rudder tabs, and related investigative/corrective actions if necessary. This AD also requires repetitive lubrication of the hinge bearings and rod end bearings of the outboard aileron balance tabs. This AD results from reports of freeplay-induced vibration of the outboard aileron balance tabs and rudder tabs. We are issuing this AD to prevent excessive vibration of the airframe during flight, which could result in divergent flutter and loss of control of the airplane.

This document revises an earlier proposed airworthiness directive (AD), applicable to certain Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) and SAAB 340B airplanes, that would have required modification of the hot detection system of the tail pipe harness of the engine nacelles. This new action revises the original NPRM by reducing the compliance time for the modification and adding repetitive inspections. The actions specified by this new proposed AD are intended to prevent false warning indications to the flightcrew from the hot detection system due to discrepancies of the harness, which could result in unnecessary aborted takeoffs on the ground or an in-flight engine shutdown. This action is intended to address the identified unsafe condition.

This action amends Title 14 Code of Federal Regulations, part 71 (14 CFR part 71) by modifying the Class E airspace area at Keokuk Municipal Airport, IA. The establishment of Area Navigation (RNAV) Global Positioning System (GPS) Instrument Approach Procedures (IAP) to Runways (RWY) 8, 14, 26 and 32 and amendments to existing Non- directional Beacon (NDB) IAPs to RWY 14 and 26 requires the modification of the Class E airspace area beginning at 700 feet above ground level (AGL). This airspace area and the legal description are modification to conform to the criteria in FAA Orders.

This action amends Title 14 Code of Federal Regulations, part 71 (14 CFR part 71) by revising Class E airspace areas at Scottsbluff, Western Nebraska Regional Airport/William B. Heilig Field, NE. The establishment of a Localizer/Distance Measuring Equipment (LOC/DME) Instrument Approach Procedure (IAP) to Runway (RWY) 12 requires the modification of the Class E airspace area beginning at 700 feet above ground level (AGL). This airspace area and the legal description are modified to conform to the criteria in the FAA Orders.

We are adopting a new airworthiness directive (AD) that supersedes AD 92-07-05, which applies to certain Raytheon Aircraft Company (Raytheon) (formerly Beech) 65, 90, 99, and 100 series airplanes. AD 92-07-05 currently requires you to inspect the rudder trim tab for proper moisture drainage provisions, and if the correct drainage provisions do not exist, before further flight, modify the rudder trim tab. This AD results from receiving and evaluating new service information that requires the actions of AD 92-07-05 for the added serial numbers LJ-1281 through LJ-1732 for the Model C90A airplanes. This AD retains all the actions of AD 92-07-05 and adds serial numbers LJ-1281 through LJ-1732 for the Model C90A airplanes in the applicability section. We are issuing this AD to prevent water accumulation in the rudder trim tab, which could result in a change in the mass properties and possibly a lower flutter speed of the airplane. A lower airplane flutter speed could result in failure and loss of control of the airplane.

The FAA is issuing this notice to advise the public of a meeting of FTCA Special Committee 202: Portable Electronic Devices.

The FAA withdraws a notice of proposed rulemaking (NPRM) proposing a new Airworthiness Directive (AD) for MD Helicopters, Inc. (MDHI) Model 600N helicopters. The NPRM proposed adding six more inspection holes in the aft fuselage skin panels and inspecting the upper and lower tailboom attachment fittings, the upper longerons, and the angles and nutplates for cracks. Also, the NPRM proposed a terminating action of modifying the fuselage aft section to strengthen the tailboom attachments and longerons. Since issuing the NPRM, we have received a report of an in-flight separation of the tailboom in the inspection area. Based on that accident and due to the critical unsafe condition, we issued a final rule; request for comments that addressed the actions proposed in the NPRM. Accordingly, we withdraw the proposed AD.

This document proposes adopting a new airworthiness directive (AD) for the specified restricted category type-certificated helicopters. The AD would require a review of the helicopter records to determine the Commercial and Government Entity (CAGE) code of the tail rotor (T/R) slider. If the T/R slider is FAA approved or has a certain legible CAGE code, this AD would require no further action. If you cannot determine whether the T/R slider is FAA approved and it has no stamped CAGE code, an illegible stamped CAGE code, or an affected CAGE code, the AD would also require, before further flight and at specified intervals, magnaflux inspecting the T/R slider for a crack. If a crack is found, the AD would require, before further flight, replacing the T/ R slider with an airworthy T/R slider. The AD would also require replacing the T/R slider with an airworthy T/R slider on or before accumulating 1,000 hours time-in-service (TIS) or on or before 12 months, whichever occurs first. This proposal is prompted by two accidents attributed to sub-standard T/R sliders that failed during flight. The actions specified by the proposed AD are intended to prevent failure of a T/R slider, loss of T/R control, and subsequent loss of control of the helicopter.

We are adopting a new airworthiness directive (AD) that supersedes AD 2002-21-08, which applies to certain Pilatus Aircraft Ltd (Pilatus) Model PC-6 airplanes. AD 2002-21-08 currently requires you to inspect the aileron assembly for correct configuration and modify as necessary. Since we issued AD 2002-21-08, the FAA determined the action should also apply to all the models of the PC-6 airplanes listed in the type certificate data sheet of Type Certificate (TC) No. 7A15 that were produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent of the applicability of AD 2002-21-08 was to apply to all the affected serial numbers of the airplane models listed in TC No. 7A15. This AD retains all the actions of AD 2002-21-08, adds those Fairchild Republic Company airplanes to the applicability of this AD, and lists the individual specific airplane models. We are issuing this AD to correct improper aileron assembly configuration, which could result in failure of the aileron mass balance weight. Such failure could lead to loss of control of the airplane.

We are adopting a new airworthiness directive (AD) that supersedes AD 98-12-01, which applies to certain Pilatus Aircraft Ltd (Pilatus) Models PC-6, PC-6/A, PC-6/B, and PC-6/C series airplanes equipped with turbo-prop engines. Since we issued AD 98-12-01, the FAA determined the action should also apply to all the models of the PC-6 airplanes listed in the type certificate data sheet of Type Certificate (TC) No. 7A15 that were produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent of the applicability of AD 98-12-01 was to apply to all the affected serial numbers of the airplane models listed in TC No. 7A15. This AD retains all the actions of AD 98-12-01, adds those Fairchild Republic Company airplanes to the applicability of this AD, and lists the individual specific airplane models. We are issuing this AD to prevent engine fuel starvation during maximum climb and descent caused by poor fuel tank venting with low fuel levels, which could result in a loss of engine power during critical phases of flight.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400 and 747-400D series airplanes. This AD requires replacing specified tie rods of the center overhead stowage bins. This AD results from manufacturer analysis of the overhead storage bin support structure that demonstrated that the capability of certain existing tie rods does not meet emergency landing load requirements. We are issuing this AD to prevent detachment of the center overhead stowage bins during an extreme forward load event, which could cause injury to passengers and hinder emergency evacuation procedures.

This action proposes special conditions for the Boeing Model 777-200 series airplanes. These airplanes, modified by Aerocon Engineering Company (AEC), will have a novel or unusual design feature associated with a forward lower lobe crew rest compartment (CRC). The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These proposed special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

This final rule changes the airman medical certification standards to disqualify an airman based on an alcohol test result of 0.04 or greater breath alcohol concentration (BAC) or a refusal to take a drug or alcohol test required by the Department of Transportation (DOT) or a DOT agency. Further, this rulemaking standardizes the time period for reporting refusals and certain test results to the FAA, and requires employers to report pre-employment and return-to-duty test refusals. It also amends the airman medical certification requirements to allow suspension or revocation of airman medical certificates for pre-employment and return-to-duty test refusals. Finally, we have updated the regulations to recognize current breath alcohol testing technology. These amendments are necessary to ensure that persons who engage in substance abuse do not operate aircraft or perform contract air traffic control duties until it is determined that these individuals can safely exercise the privileges of their certificates.

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model MD-11 and -11F airplanes. The existing AD currently requires an initial general visual inspection of the power feeder cables of the integrated drive generator (IDG) and the fuel feed lines of engine pylons No. 1 and No. 3 on the wings for proper clearance and damage; corrective actions if necessary; and repetitive general visual inspections and a terminating action for the repetitive inspections. This proposed AD would continue to require the existing actions, and for certain airplanes, this proposed AD would require installation of new clamps on the power feeder cables of the IDG of engine pylons No. 1 and No. 3. This proposed AD results from reports of IDG power feeder cables riding against structure and fuel lines in the No. 1 and No. 3 pylons. We are proposing this AD to prevent potential chafing of the power feeder cables of the IDG in engine pylons No. 1 and No. 3 on the wings, and consequent arcing on the fuel lines in the engine pylons and possible fuel fire.

The FAA proposes to adopt a new airworthiness directive (AD) for all Fokker Model F27 Mark 500 airplanes. This proposed AD would require an inspection to determine whether certain main landing gear (MLG) drag stay units (DSUs) are installed. This proposed AD would also require an ultrasonic inspection to determine if certain tubes are installed in the affected DSUs of the MLG, and related investigative/ corrective actions if necessary. This proposed AD results from a report that, due to fatigue cracking from an improperly machined radius of the inner tube, a drag stay broke, and, consequently, led to the collapse of the MLG during landing. We are proposing this AD to prevent such fatigue cracking, which could result in reduced structural integrity or collapse of the MLG.

We are adopting a new airworthiness directive (AD) to revise AD 68-17-03, which applies to all Pilatus Aircraft Ltd. (Pilatus) PC-6 series airplanes. AD 68-17-03 requires you to repetitively inspect the rudder end rib for cracks and replace the rudder end rib with a modified rudder end rib when you find cracks. Installing the modified rudder end rib terminates the repetitive inspection requirements of AD 68-17-03. Under a licensing agreement with Pilatus, Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation) produced Model PC-6 series airplanes (manufacturer serial numbers 2001 through 2092) in the United States. AD 68-17-03 was intended to apply to all affected serial numbers of Model PC-6 series airplanes listed on Type Certificate Data Sheet (TCDS) No. 7A15, including the Fairchild-produced airplanes. Consequently, this AD clarifies that all models of the PC-6 airplane on TCDS No. 7A15 (including those models produced under the licensing agreement by Fairchild Republic Company) are included in the applicability. We are issuing this AD to detect and correct cracks in the rudder end rib, which could result in failure of the rudder end rib. This failure could result in loss of rudder control.

We are adopting a new airworthiness directive (AD) that supersedes AD 2005-26-53, which applies to certain Pacific Aerospace Corporation Ltd. (PAC) 750XL airplanes. AD 2005-26-53 currently requires you to insert text into the Limitations Section of the Airplane Flight Manual (AFM) that reduces the maximum takeoff weight from 7,500 pounds to 7,125 pounds. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand and the FAA's decision that the actions correct an unsafe condition. Consequently, this AD would require you to remove rivets that have not been fully age hardened and replace them with bolts, washers, and nuts in specific locations where reduction in rivet strength affects overall structural capability. This AD retains the actions of the previous AD until the rivets are replaced with the bolts, washers, and nuts. We are issuing this AD so that wing ultimate load requirements are met. If wing ultimate load requirements are not met, wing failure could result with consequent loss of control of the airplane.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A310-300 airplanes. This proposed AD would require replacing the existing non-return valve (NRV) of the auxiliary center tanks (ACTs) of the fuel system with a new, improved NRV. This proposed AD results from a report that it was not possible to transfer fuel from ACTs 1 and 2 during flight, and no electronic centralized aircraft monitor warnings were triggered. Investigation revealed a faulty static inverter and blown fuse, resulting in failure of certain fueling bus bars and subsequent failure of the automatic ACT fuel transfer. We are proposing this AD to prevent these failures, combined with failure of the NRV to close. If the NRV is open during flight, the fuel supply to the engines may be reduced during cross-feed operation to the extent that fuel starvation could occur and result in engine flameout.

Pursuant to FAA's rulemaking provisions governing the application, processing, and disposition of petitions for exemption part 11 of Title 14, Code of Federal Regulations (14 CFR), this notice contains a summary of certain petitions seeking relief from specified requirements of 14 CFR. The purpose of this notice is to improve the public's awareness of, and participation in, this aspect of FAA's regulatory activities. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of any petition or its final disposition.

The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model ERJ 170 airplanes. This AD requires inspecting for excess sealant applied to the attachment bolts of the negative pressure relief valve, and performing corrective actions if necessary. This AD results from reports that excess sealant was applied to the attachment bolts of the negative pressure relief valve, which interfered with the valve's movable diaphragm. We are issuing this AD to prevent incorrect operation of the negative pressure relief valve, which could result in negative pressures that exceed the structural strength limits of the airframe and lead to reduced structural integrity of the airplane.

These special conditions are issued to Sagem Avionics, Inc., 16923 Meridian East, Puyallup, WA 98375, for a Supplemental Type Certificate for the Cessna C-180 airplane. This airplane will have novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. This novel and unusual design feature will include the installation of a two panel electronic display system, or Electronic Flight Instrument System (EFIS), manufactured by Sagem. The installation also includes components associated with this display system. The applicable regulations do not contain adequate or appropriate airworthiness standards for the protection of these systems from the effects of high intensity radiated fields (HIRF). These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to the airworthiness standards applicable to these airplanes.