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COURTHOUSE NEWS SERVICE

Federal Regulation Brief

January 2, 2008

TRANSPORTATION

Today’s Brief Includes (Nov 28 – Jan 1):

National Transportation Safety Board (NTSB) – no newly published regulations this month

Transportation (DOT)

TRANSPORTATION (DOT)

NEWLY PUBLISHED REGULATIONS

FEDERAL AVIATION ADMINISTRATION (FAA)

Air carrier certification and operations, transport category airplanes, enhanced airworthiness program for airplane systems and fuel tank safety,

correction: Enhanced Airworthiness Program for Airplane Systems/Fuel Tank Safety

(EAPAS/FTS), Federal Register, December 5, 2007, Volume 72, Number 233,

CORRECTIONS, Page 68618, 14 CFR Part 26, Docket No. FAA-2004-18379;

Amendment Nos. 1-60, 21-90, 25-123, 26-0, 91-297, 121-336, 125-53, 129-43, RIN

2120-AI31, correction.

[TEXT] [PDF]

CORRECTION: In rule document E7-21434 beginning on page 63364 in the issue of

November 8, 2007, the following correction is made:

Section 26.11 [Corrected]

On page 63410, in Section 26.11(d)(5), in the first column, in the sixth line,

“December 10, 2009” should read “June 7, 2010”.

Airworthiness directives, Agusta S.p.A. AB139 and AW139 helicopters:

Airworthiness Directives; Agusta S.p.A. Model AB139 and AW139 Helicopters,

Federal Register, December 10, 2007, Volume 72, Number 236, Rules and

Regulations, Page 69595, 14 CFR Part 39, Docket No. FAA-2007-0285, Directorate

Identifier 2007-SW-15-AD, Amendment 39-15296, AD 2007-25-14, RIN 2120-AA64,

Final rule request for comments.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective December 26, 2007. The Director of the Federal Register approves the incorporation by reference of Agusta Bollettino

Tecnico No. 139-069, Revision A, dated November 8, 2006, as of December 26,

2007. The Federal Aviation Administration (FAA) must receive any public comments on this AD by February 8, 2008.)

PURPOSE: This airworthiness directive (AD) requires actions intended to address the unsafe condition described in the summary, below.

SUMMARY: The Federal Aviation Administration (FAA) supersedes an existing airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB139 helicopters.

This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority to identify and correct an unsafe condition on an aviation product. The aviation authority of Italy, with which the FAA has a bilateral agreement, states in the MCAI:

Field reports have shown that the Agusta AB/AW139's Tailpipe Assembly is prone to cracks. To prevent any cracks from developing into failure of the exhaust tailpipe assembly * * *

This AD retains the requirements of the existing AD, but expands the list of aircraft that must follow the AD to include the Agusta Model AW139 helicopters, and includes modification procedures to strengthen certain cracked areas that are outside the cowling and are within certain allowable limits.

THIS REGULATION IS NOT FURTHER ANALYZED HERE. IF YOU NEED MORE

INFORMATION, PLEASE SEE THE FULL TEXT OF THE REGULATION IN THE LINKED

DOCUMENT.

Airworthiness directives, Aircraft Industries: Airworthiness Directives; Aircraft

Industries, a.s. (Type Certificate No. G24EU Formerly Held by LETECKÉ ZÁVODY a.s. and LET Aeronautical Works) Model L-13 Blanik Gliders, Federal Register, December

3, 2007, Volume 72, Number 231, Rules and Regulations, Page 67841, 14 CFR Part

39, Docket No. FAA-2007-28980 Directorate Identifier 2007-CE-071-AD, Amendment

39-15282, AD 2007-25-01, RIN 2120-AA64, Final Rule.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective January 7, 2008. As of January 7,

2008, the Director of the Federal Register approves the incorporation by reference of certain publications listed in this AD.)

PURPOSE: This airworthiness directive (AD) requires actions intended to correct the unsafe condition described in the summary, below.

SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for Aircraft

Industries, a.s. (Type Certificate No. G24EU Formerly Held by LETECKÉ ZÁVODY a.s. and LET Aeronautical Works) Model L-13 Blanik gliders. This AD results from mandatory continuing airworthiness information (MCAI) issued 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:

This Airworthiness Directive (AD) is prompted by the discovery of cracks on

L13 BLANIK sailplanes in zones where the forward and aft control sticks are attached to the connecting rod, designated as “control bridge” in the relevant

Illustrated Parts Catalogues (IPC). If left uncorrected, cracks could propagate and lead to failure of the connecting rod with subsequent loss of control of the sailplane.



DOCUMENT.

Airworthiness directives, Airbus A300 and A300-600: Airworthiness Directives;

Airbus Model A300 Series Airplanes and Model A300-600 Series Airplanes, Federal

Register, December 10, 2007, Volume 72, Number 236, Rules and Regulations, Page

69601, 14 CFR Part 39, Docket No. FAA-2007-27257, Directorate Identifier 2006-

NM-131-AD, Amendment 39-15297, AD 2007-25-15, RIN 2120-AA64, Final rule.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective January 14, 2008. The Director of the

Federal Register approves the incorporation by reference of certain publications listed in the AD as of January 14, 2008.)

PURPOSE: This airworthiness directive (AD) results from a report of a failure of a sliding rod of the main landing gear (MLG) retraction actuator before the actuator reached the life limit established by the manufacturer in Airbus Model A300 series airplanes; and all Airbus Model A300-600 series airplanes. This AD requires actions intended to prevent failure of the sliding rod of the MLG retraction actuator, which could result in reduced structural integrity of the MLG.

SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for all

Airbus Model A300 series airplanes and all Airbus Model A300-600 series airplanes.

This AD requires inspecting to determine the part number of the sliding rods of the

MLG retraction actuators. For MLG retraction actuators equipped with sliding rods having certain part numbers, the AD also requires inspecting for discrepancies, including but not limited to cracking, of the sliding rod; and performing corrective actions if necessary. This AD also requires returning affected sliding rods to the manufacturer.



DOCUMENT.

Airworthiness directives, Airbus A300, A300-600, and A310: Airworthiness

Directives; Airbus Model A300 Series Airplanes, Model A300-600 Series Airplanes, and Model A310 Series Airplanes, Federal Register, December 10, 2007, Volume 72,

Number 236, Rules and Regulations, Page 69610, 14 CFR Part 39, Docket No. FAA-

2007-27982, Directorate Identifier 2007-NM-009-AD, Amendment 39-15288, AD

2007-25-06, RIN 2120-AA64, Final rule.

[TEXT] [PDF]


Federal Register approves the incorporation by reference of certain publications listed in this AD as of January 14, 2008.)


SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for Airbus

Model A300 series airplanes, Model A300-600 series airplanes, and Model A310 series airplanes. 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:

* * * accidents which occurred to in-service aircraft caused by the violent opening of a passenger door, related to excessive residual pressurization in the cabin on ground.

* * * * *

This unsafe condition could result in injury to crew members opening the passenger door.



DOCUMENT.

Airworthiness directives, Airbus A310: Airworthiness Directives; Airbus Model

A310 Series Airplanes, Federal Register, December 10, 2007, Volume 72, Number

236, Rules and Regulations, Page 69598, 14 CFR Part 39, Docket No. FAA-2007-

29117, Directorate Identifier 2007-NM-114-AD, Amendment 39-15291, AD 2007-25-

09, RIN 2120-AA64, Final rule.

[TEXT] [PDF]


Federal Register approves the incorporation by reference of a certain publication listed in this AD as of January 14, 2008.)

PURPOSE: This airworthiness directive (AD) requires actions to correct the unsafe condition described in the summary, below.


Model A310 Series airplanes. 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:

As a result of a Wide Spread Fatigue Damage (WFD) calculation on A310 aircraft it was found that a modification of the upper fuselage circumferential joint at FR (frame) 55/58 is necessary to enable the aircraft to reach the

Extended Service Goal (ESG).

The unsafe condition is failure of the circumferential joint of the upper fuselage, which could result in reduced structural integrity of the airplane.



DOCUMENT.


A310 Series Airplanes, Federal Register, December 10, 2007, Volume 72, Number




[TEXT] [PDF]



PURPOSE: This airworthiness directive (AD) results from issuance of new and revised structural inspections and inspection intervals for Airbus Model A310 series airplanes.

This AD requires actions intended to detect and correct fatigue cracking, which could result in reduced structural integrity.

SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for all Airbus

Model A310 series airplanes. This AD requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new and revised structural inspections and inspection intervals.



DOCUMENT.

Airworthiness directives, Airbus A318, A319, A320, and A321: Airworthiness

Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes, Federal




[TEXT] [PDF]





Model A318, A319, A320, and A321 series airplanes. 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:

After a push back from the gate, an A320-200 aircraft was preparing to initiate taxi, when a NLG (nose landing gear) uncommanded retraction occurred, and then the aircraft abruptly hit the ground.

* * * Untimely unlocking and/or retraction of the NLG, while on the ground, could cause injury to ground personnel and significant structural damage to the airplane.



DOCUMENT.


A330 Airplanes, Federal Register, December 3, 2007, Volume 72, Number 231, Rules and Regulations, Page 67845, 14 CFR Part 39, Docket No. FAA-2007-0269,

Directorate Identifier 2007-NM-158-AD, Amendment 39-15287, AD 2007-25-05, RIN

2120-AA64, Final rule, request for comments.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective December 18, 2007. The Director of the Federal Register approves the incorporation by reference of a certain publication, listed in the AD as of December 18, 2007. The Federal Aviation Administration (FAA) must receive any comments on this AD by January 2, 2008.)



Model A330 airplanes. 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 discovered that a batch of sleeves and pins of the Rolls-Royce

Trent 700 Thrust Reverser Unit (TRU) hinge n˚5 has not been subjected to the correct precipitation hardening.

This production quality issue, if not corrected, can lead to the complete failure of the hinge n˚5--the remaining hinges may not sustain ultimate load-resulting in the worst case to the TRU release from the pylon, which constitutes an unsafe condition.

The degradation of the mechanical specifications of these parts puts into question the current design life goal of these parts. * * *

The unsafe condition is possible detachment of the thrust reverser unit from the airplane, which could result in reduced controllability and possible damage to the airplane.



DOCUMENT.

Airworthiness directives, Bell Helicopter Textron Canada Ltd. 206A and

206B helicopters: Airworthiness Directives; Bell Helicopter Textron Canada Limited

Model 206A and 206B Helicopters, Federal Register, December 10, 2007, Volume 72,


2007-28690, Directorate Identifier 2006-SW-21-AD, Amendment 39-15289, AD

2007-25-07, RIN 2120-AA64, Final rule.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective January 14, 2008. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of January 14, 2008.)

PURPOSE: This airworthiness directive (AD) results from an accident in which the fin supports failed in certain Bell Helicopter Textron Canada Limited (BHTC) Model 206A and 206B helicopters, serial numbers (S/N) 0004 through 3906, with two-piece vertical stabilizer (fin) supports (fin supports) installed. This AD requires actions intended to detect improper torque of the fin supports' attachment hardware, gaps between the fin support bracket and the doubler, painted mating surfaces of the fin supports, vertical fin, and vertical fin inserts (fin inserts), and cracking in the fin

supports, to prevent the vertical fin from rotating into the tail rotor, separation of the tail rotor, and subsequent loss of control of the helicopter.

SUMMARY: This amendment adopts a new AD for Bell Helicopter Textron Canada

Limited (BHTC) Model 206A and 206B helicopters, serial numbers (S/N) 0004 through 3906, with two-piece vertical stabilizer (fin) supports (fin supports) installed, that requires inserting a revision into the applicable maintenance manual, verifying the torque on the fin support attachment hardware, inspecting the fin support bracket and fins for paint or gaps, and inspecting the fin support bracket for cracking, and if a crack is found, replacing the two-piece vertical fin support with a one-piece casting support.



DOCUMENT.

Airworthiness directives, Boeing 737-100, -200, -200C, -300, -400, and -

500: Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and

-500 Series Airplanes, Federal Register, December 17, 2007, Volume 72, Number




[TEXT] [PDF]



PURPOSE: This airworthiness directive (AD) results from a report that an operator found multiple cracks in the fuselage skin of a Model 737-200 airplane, at the forward fastener row of the STA 259.5 circumferential butt splice between stringers

19 and 24. This AD requires actions intended to prevent cracking of the STA 259.5 circumferential butt splice, which could result in loss of structural integrity of the fuselage skin and possible loss of cabin pressure.

SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for certain

Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive detailed and high-frequency eddy current inspections for cracking around the heads of the fasteners on the forward fastener row of certain areas of the station (STA) 259.5 circumferential butt splice, and repair if necessary. This AD also requires a preventive modification, which eliminates the need for the repetitive inspections.



DOCUMENT.

Airworthiness directives, Boeing 737-600, -700, -700C, -800, and -900:

Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, and -900 Series

Airplanes, Federal Register, December 10, 2007, Volume 72, Number 236, Rules and


Identifier 2007-NM-130-AD, Amendment 39-15284, AD 2007-25-03, RIN 2120-

AA64, Final rule.

[TEXT] [PDF]


Federal Register approves the incorporation by reference of a certain publication listed in the AD as of January 14, 2008.)

PURPOSE: This airworthiness directive (AD) results from web oil can conditions found on the aft pressure bulkhead of several Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires actions intended to detect and correct oil can conditions, bulges, or previous repairs in the aft pressure bulkhead, which could lead to web cracks and consequently result in rapid decompression of the airplane.


Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires repetitive inspections of either the aft side or forward side of the aft pressure bulkhead for oil can conditions or bulges, a one-time inspection of the aft pressure bulkhead to identify any previously installed web repair, and corrective actions if necessary.



DOCUMENT.

Airworthiness directives, Boeing 747-100, 747-100B, 747-100B SUD, 747-

200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP: Airworthiness

Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C,

747-200F, 747-300, 747SR, and 747SP Series Airplanes, Federal Register, December


39, Docket No. FAA-2007-28620, Directorate Identifier 2007-NM-090-AD,

Amendment 39-15299, AD 2007-25-17, RIN 2120-AA64, Final rule.

[TEXT] [PDF]



PURPOSE: This airworthiness directive (AD) results from a report that an operator found a 1.65-inch crack on the station (STA) 1241 bulkhead fitting on the left side of a Boeing Model 747-200F series airplane that had accumulated 17,332 total flight cycles. This AD requires actions intended to detect and correct cracking in the STA

1241 bulkhead fittings, which could result in reduced structural integrity of the airplane.


Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F,

747-300, 747SR, and 747SP series airplanes. This AD requires repetitive inspections for cracking of the STA 1241 bulkhead fittings just above the canted pressure deck; a one-time determination of the edge margin at seven fastener positions on each side of the airplane; and related investigative/corrective actions if necessary.



DOCUMENT.

Airworthiness directives, Boeing 747-200B, 747-300, 747-400, 747-400D,

and 747-400F: Airworthiness Directives; Boeing Model 747-200B, 747-300, 747-

400, 747-400D, and 747-400F Series Airplanes Equipped with General Electric CF6-

80C2 Engines, Federal Register, December 28, 2007, Volume 72, Number 248, Rules and Regulations, Page 73587, 14 CFR Part 39, Docket No. FAA-2007-28352,


2120-AA64, Final rule.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective February 1, 2008. The Director of the

Federal Register approves the incorporation by reference of a certain publication listed in the AD as of February 1, 2008.)

PURPOSE: This airworthiness directive (AD) results from two reports of missing flipper doors for the engine core cowls in certain Boeing Model 747-200B, 747-300,

747-400, 747-400D, and 747-400F series airplanes. This AD requires actions intended to detect and correct migrated hinge pins and damaged flipper doors, which could allow the flipper door to fall off, resulting in the potential for an engine fire to move into the flammable leakage zone of the strut and for the amount of fire extinguishing agent reaching the fire to be diluted, and subsequent uncontained fire in the engine strut.


Boeing Model 747-200B, 747-300, 747-400, 747-400D, and 747-400F series airplanes. This AD requires repetitive inspections of the left- and right-hand flipper door assemblies of the engine core cowls for migrated pins and damaged flipper doors, and corrective actions if necessary. Appropriate modification of the hinge assemblies allows you to stop performing the repetitive inspections.



DOCUMENT.

Airworthiness directives, Boeing 747-200B, 747-300, and 747-400:

Airworthiness Directives; Boeing Model 747-200B, 747-300, and 747-400 Series




AA64, Final rule, request for comments.

[TEXT] [PDF]


Federal Register approves the incorporation by reference of a certain publication listed in the AD as of January 2, 2008. The Federal Aviation Administration (FAA) must receive any public comments on this AD by February 15, 2008.)

PURPOSE: This airworthiness directive (AD) results from a report that several passenger masks with broken in-line flow indicators were found following a mask

deployment. This AD requires actions intended to prevent the in-line flow indicators of the passenger oxygen masks from fracturing and separating, which could inhibit oxygen flow to the masks and consequently result in exposure of the passengers and cabin attendants to hypoxia following a depressurization event.


Boeing Model 747-200B, 747-300, and 747-400 series airplanes. This AD requires an inspection to determine the manufacturer and manufacture date of the oxygen masks in the passenger service units of the outboard and center main deck, the flight attendant service units, flightcrew rest, upper and lower module of the door 5 overhead crew rest, lavatory modules, and miscellaneous ceiling panels, as applicable, and related investigative/corrective actions if necessary.



DOCUMENT.

Airworthiness directives, Boeing 747-200C and -200F: Airworthiness

Directives; Boeing Model 747-200C and -200F Series Airplanes, Federal Register,

December 17, 2007, Volume 72, Number 241, Rules and Regulations, Page 71218,

14 CFR Part 39, Docket No. FAA-2007-28924, Directorate Identifier 2007-NM-051-

AD, Amendment 39-15305, AD 2007-26-03, RIN 2120-AA64, Final rule.

[TEXT] [PDF]



PURPOSE: This airworthiness directive (AD) results from reports of water contamination in the electrical/electronic units in the main equipment center. This AD requires actions intended to prevent water contamination of the electrical/electronic units, which could cause the electrical/electronic units to malfunction, and as a consequence, could adversely affect the airplane's continued safe flight.

SUMMARY: The Federal Aviation Administration (FAA) adopts a new airworthiness directive (AD) for certain Boeing Model 747-200C and -200F series airplanes. This AD requires, among other actions, installing mounting brackets, support angles, and moisture curtains in the main equipment center.



DOCUMENT.

Airworthiness directives, Boeing 747-400: Airworthiness Directives; Boeing

Model 747-400 Series Airplanes, Federal Register, December 10, 2007, Volume 72,



2007-25-19, RIN 2120-AA64, Final rule, request for comments.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective December 26, 2007. The Director of the Federal Register approves the incorporation by reference of a certain publication

listed in the AD as of December 26, 2007. The Federal Aviation Administration (FAA) must receive any public comments on this AD by February 8, 2008.)

PURPOSE: This airworthiness directive (AD) results from a report of an uncommanded up and down pitch movement of an airplane in flight and resistance in the elevator controls on the ground during taxi in certain Boeing Model 747-400 series airplanes. This AD requires actions intended to prevent cracking and buckling of the forward or rear heat exchanger shell of the air distribution system of the crew rest area, which could result in jamming of the rudder and/or elevator control cables and consequent reduced controllability of the airplane.


Boeing Model 747-400 series airplanes. This AD requires repetitive inspections to detect discrepancies of the forward and rear heat exchanger shells of the air distribution system of the crew rest area, and applicable corrective actions. This AD also requires an inspection to identify the part number, shop code, and build date of the forward and rear heat exchanger shells of the air distribution system of the crew rest area, and applicable corrective actions, which end the repetitive inspections.



DOCUMENT.

Airworthiness directives, Boeing 747-400 and 747-400D: Airworthiness

Directives; Boeing Model 747-400 and 747-400D Series Airplanes, Federal Register,


14 CFR Part 39, Docket No. FAA-2007-0301, Directorate Identifier 2007-NM-069-AD,

Amendment 39-15300, AD 2007-25-18, RIN 2120-AA64, Final rule, request for comments.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective December 26, 2007. The Director of the Federal Register approves the incorporation by reference of a certain publication listed in this AD as of December 26, 2007. The Federal Aviation Administration (FAA) must receive any public comments on this AD by February 8, 2008.)

PURPOSE: This airworthiness directive (AD) results from a report indicating that the overhead lateral shear beam aft of main entry door number 5 reacts to certain loads from the weight of the center stowage bins of zone E and additional loads in certain

Boeing Model 747-400 and 747-400D series airplanes. This AD requires actions intended to prevent detachment of the center stowage bins of zone E at forward load levels less than 9g during an emergency landing, which could cause injury to passengers and/or crew and could impede subsequent rapid evacuation.


Boeing Model 747-400 and 747-400D series airplanes. For certain airplanes, this AD requires modifying the stowage bin ladder of zone E, installing new intercostals, removing existing tie rods, and installing new tie rods. For certain other airplanes, this AD requires modifying the lateral shear beam.



DOCUMENT.

Airworthiness directives, Boeing 757-200, -200CB, and -300: Airworthiness

Directives; Boeing Model 757-200, -200CB, and -300 Series Airplanes, Federal




[TEXT] [PDF]


Federal Register approves the incorporation by reference of a certain publication listed in this AD as of January 22, 2008. The Federal Aviation Administration (FAA) must receive any public comments on this AD by January 22, 2008.)

PURPOSE: This airworthiness directive (AD) results from reports of cracked intercostal tee clips at the number 3 and number 4 doorstops of the passenger door cutouts in certain Boeing Model 757-200, -200CB, and -300 series airplanes. This AD requires actions intended to detect and correct cracking of the tee clips, which could result in additional stress on the adjacent tee clips, surrounding intercostals, edge frame, door structure and doorstops. This additional stress could cause further cracking or breaking of the tee clips, which could result in failure of the door to seal and consequent rapid decompression of the airplane.


Boeing Model 757-200, -200CB, and -300 series airplanes. This AD requires repetitive detailed inspections with a borescope for cracks of the intercostal tee clips; or repetitive detailed inspections for cracks of the intercostal tee clips and attachment fasteners at the number 3 and number 4 doorstops of the passenger door cutouts; and related investigative and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections.



DOCUMENT.

Airworthiness directives, Boeing 767: Airworthiness Directives; Boeing Model

767 Airplanes, Federal Register, November 28, 2007, Volume 72, Number 228, Rules and Regulations, Page 67236, 14 CFR Part 39, Docket No. FAA-2007-29259,


2120-AA64, Final rule.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective November 28, 2007. The Director of the Federal Register approves the incorporation by reference of certain publications listed in the AD as of November 28, 2007.)

PURPOSE: This airworthiness directive (AD) results from reports of freeplay-induced vibration of the rudder and the elevator in certain Boeing Model 767 airplanes. The potential for vibration of the control surface should be avoided because the point of transition from vibration to divergent flutter is unknown. This AD requires actions intended to prevent excessive vibration of the airframe during flight, which could result in loss of control of the airplane.

SUMMARY: The Federal Aviation Administration (FAA) supersedes an existing AD that applies to all Boeing Model 767 airplanes. That AD currently requires repetitive measurements of the rudder and elevator freeplay, repetitive lubrications of rudder and elevator components, and related investigative/corrective actions if necessary.

This new AD instead requires revised repetitive measurements of the rudder freeplay and the elevator freeplay for each of the power control actuators (PCAs) that move the rudder and elevator, corrective and related investigative actions if necessary, and repetitive lubrications of the rudder and elevator components. For some airplanes, this AD also requires related concurrent actions.



DOCUMENT.

Airworthiness directives, Boeing 767-300F: Airworthiness Directives; Boeing

Model 767-300F Series Airplanes, Federal Register, December 10, 2007, Volume 72,



2007-25-13, RIN 2120-AA64, Final rule.

[TEXT] [PDF]



PURPOSE: This airworthiness directive (AD) results from a report of failures of the duct joint seal of the mix manifold system. This AD requires actions intended to prevent air conditioning leakage into the mix manifold bay. Such leakage could decrease the air flow to the flight compartment and main cabin or could allow smoke into the flight compartment in the event of a fire in the main cabin or forward cargo compartment.


Boeing Model 767-300F series airplanes. This AD requires replacing the rotomolded duct(s) of the mix manifold system with new duct(s).



DOCUMENT.

Airworthiness directives, Boeing 777-200, -200LR, -300, and -300ER:

Airworthiness Directives; Boeing Model 777-200, -200LR, -300, and -300ER Series




AA64, Final rule.

[TEXT] [PDF]



PURPOSE: This airworthiness directive (AD) results from a report that a cracked left elevator actuator fitting was found on a Model 777 airplane. This AD requires actions intended to detect and correct a cracked actuator fitting, which could detach from the elevator and lead to an unrestrained elevator and an unacceptable flutter condition, which could result in loss of airplane control.

SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for all Boeing

Model 777-200, -200LR, -300, and -300ER series airplanes. This AD requires doing initial and repetitive inspections for cracking of the elevator actuator fittings, and replacing any cracked fitting with a new fitting.



DOCUMENT.

Airworthiness directives, Cirrus Design Corp. SR22: Airworthiness Directives;

Cirrus Design Corporation Model SR22 Airplanes, Federal Register, November 29,

2007, Volume 72, Number 229, Rules and Regulations, Page 67566, 14 CFR Part 39,

Docket No. FAA-2007-0250, Directorate Identifier 2007-CE-091-AD, Amendment 39-

15279, AD 2007-24-13, RIN 2120-AA64, Final rule, request for comments.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective December 4, 2007. On December 4,

2007, the Director of the Federal Register approves the incorporation by reference of certain publications listed in this AD. The Federal Aviation Administration (FAA) must receive any comments on this AD by January 28, 2008.)

PURPOSE: This airworthiness directive (AD) results from reports of pilots' inability to move the aileron control without using excessive force when flying in freezing conditions in certain Cirrus Design Corporation Model SR22 airplanes. Moisture from a prior rain shower entered through a gap at the interface of the left and right outboard wing tips and wing structure. The moisture traveled along the aft wing shear web, accumulated below the aileron control pulley, and froze at an altitude with an outside air temperature below freezing. When this moisture is exposed to freezing conditions, operation of the aileron control pulley is impaired. This AD requires actions intended to prevent moisture from accumulating along the wing shear web where it may freeze in certain conditions. This condition could result in operational failure of the aileron control pulley, which could lead to loss of control.


Cirrus Design Corporation (Cirrus) Model SR22 airplanes. This AD requires installation of a drain hole in each of the left and right outboard wing tips.



DOCUMENT.

Airworthiness directives, Dassault Mystere-Falcon 50, Mystere-Falcon 900,

Falcon 900EX, Falcon 2000, and Falcon 2000EX: Airworthiness Directives;

Dassault Model Mystere-Falcon 50, Mystere-Falcon 900, Falcon 900EX, Falcon 2000, and Falcon 2000EX Airplanes, Federal Register, December 10, 2007, Volume 72,



2007-25-10, RIN 2120-AA64, Final rule.

[TEXT] [PDF]




SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for Dassault

Model Mystere-Falcon 50, Mystere-Falcon 900, Falcon 900EX, Falcon 2000, and

Falcon 2000EX airplanes. 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:

A rotating rod in the trailing edge flap control linkage broke in flight.

Investigations revealed that the rotating rod had been installed in the wrong side during a maintenance operation. This incorrect installation caused a contact between the rotating rod and its retaining bracket leading, after some time in operation, to the rod breakage and flap asymmetry situation.

The consequence on the airplane of the flap asymmetry combined with a latent failure of the asymmetry detection system is classified as a catastrophic failure condition.

The unsafe condition is failure of the rotating rod in the control linkage of the trailing edge flap and consequent flap asymmetry during the approach to landing, which could result in reduced controllability of the airplane.



DOCUMENT.

Airworthiness directives, Empresa Brasileira de Aeronautica S.A. (EMBRAER)

EMB-135ER, -135KE, -135KL, -135LR, and EMB-145, -145ER, -145MR, -

145LR, -145XR, -145MP, and -145EP: Airworthiness Directives; Empresa

Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135ER, -135KE, -135KL, and -

135LR Airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes, Federal Register, November 28, 2007, Volume 72, Number




[TEXT] [PDF]




SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for Empresa

Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135ER, -135KE, -135KL, and -

135LR airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. 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 the development of cracks in the forward fuselage right hand (RH) side skin during full-scale fatigue tests. Those cracks may quickly reach their critical length, reducing the aircraft structural integrity, with possible rapid decompression of the aircraft.



DOCUMENT.

Airworthiness directives, Eurocopter France SA-365 N1, AS-365 N2, AS-365

N3, SA-366G1, EC 155B, and EC155B1 helicopters: Airworthiness Directives;

Eurocopter France Model SA-365 N1, AS-365 N2, AS-365 N3, SA-366G1, EC 155B, and EC155B1 Helicopters, Federal Register, December 10, 2007, Volume 72, Number


28448, Directorate Identifier 2006-SW-24-AD, Amendment 39-15290, AD 2007-25-


[TEXT] [PDF]

(This airworthiness directive (AD) is effective January 14, 2008.)

PURPOSE: This amendment is prompted by the finding that metal chips were not detected on the magnetic plug due to insufficient oil flow because the oil in the TGB was being maintained at the minimum level in Eurocopter France Model SA-365 N1,

AS-365 N2, AS-365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. This airworthiness directive (AD) requires actions intended to detect metal chips on the magnetic plug, to prevent damage to the bearing resulting in end play, loss of T/R pitch control, and subsequent loss of control of the helicopter.

SUMMARY: This amendment supersedes an existing AD for the specified Eurocopter

France (ECF) model helicopters. That AD currently requires a onetime inspection for end play in the pitch control rod assembly double bearing (bearing) using the tail rotor (T/R) hub control plate, and before further flight, replacing the bearing if end play is present. This amendment requires checking the T/R gearbox (TGB) oil level before the first flight of the day and maintaining the oil at the maximum level for certain helicopters. Also, this action requires, during each required inspection or at certain specified intervals, ensuring the oil is at the maximum level for certain other model helicopters. This action also requires inspecting the magnetic plug for chips at specified intervals. Depending on the quantity of chips found, this action requires either replacing the TGB before further flight or further inspecting for axial play in the T/R hub pitch change control spider (spider). If axial play is found in the spider, before further flight, this AD requires replacing the bearing.



DOCUMENT.

Airworthiness directives, Fokker F27 Mark 050: Airworthiness Directives;

Fokker Model F27 Mark 050 Airplanes, Federal Register, December 3, 2007, Volume

72, Number 231, Rules and Regulations, Page 67847, 14 CFR Part 39, Docket No.

FAA-2007-0268, Directorate Identifier 2007-NM-129-AD, Amendment 39-15286, AD

2007-25-04, RIN 2120-AA64, Final rule, request for comments.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective December 18, 2007. The Director of the Federal Register approves the incorporation by reference of a certain publication, listed in the AD as of December 18, 2007. The Federal Aviation Administration (FAA) must receive any comments on this AD by January 2, 2008.)


SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for Fokker

Model F27 Mark 050 airplanes. 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:

During scheduled MRB (maintenance review board) mid-life X-ray inspections of Fokker 50 (F27 Mark 050) engine mount frames, severe internal corrosion of the tubes was discovered. In some locations, the depth of the corrosion spots appeared to be more than 50 percent of material thickness. * * * This condition, if not corrected, could ultimately lead to failure of the engine mounting frame in cases where multiple tubes are severely affected. * * *



DOCUMENT.

Airworthiness directives, Fokker F.28 Mark 0070 and 0100: Airworthiness

Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes, Federal Register,




[TEXT] [PDF]




SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for Fokker

Model F.28 Mark 0070 and 0100 airplanes. 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.


Two events have been reported of Fokker 100 (F.28 Mk.0100) aircraft, where the Nose Landing Gear (NLG) failed to extend in the normal mode and problems were experienced to open the NLG doors, almost preventing extension of the NLG in the emergency (alternate) mode. Subsequent investigation and tests have shown that the friction of the bearing in the roller of the NLG Door Uplock Bracket Assembly is high, causing increased resistance in the mechanical system that unlocks the NLG doors. This condition, if not corrected, may result in a NLG up landing, which is considered a hazardous event. * * *



DOCUMENT.

Airworthiness directives, General Electric Co. CF6-80C2B1 turbofan engine:

Airworthiness Directives; General Electric Company (GE), Federal Register,

November 28, 2007, Volume 72, Number 228, Rules and Regulations, Page 67240,

14 CFR Part 39, Docket No. FAA-2007-0193, Directorate Identifier 2007-NE-43-AD,

Amendment 39-15273, AD 2007-24-07, RIN 2120-AA64, Final rule, request for comments.

[TEXT] [PDF]


Federal Register approves the incorporation by reference of certain publications listed in the regulations as of January 2, 2008. The Federal Aviation Administration (FAA) must receive any comments on this AD by January 28, 2008.)

PURPOSE: This airworthiness directive (AD) results from a report that a repair shop did not meet the process requirements when applying copper-nickel-indium (Cu-Ni-

In) thermal coating to certain stage 1 fan disks in a certain General Electric Company

(GE) CF6-80C2B1 turbofan engine. This AD requires actions intended to prevent possible uncontained release of multiple fan blades, resulting in damage to the airplane.

SUMMARY: The Federal Aviation Administration (FAA) adopts a new airworthiness directive (AD) for a GE CF6-80C2B1 turbofan engine, serial number (SN) 690203, with fan disk, part number (P/N) 1703M78P11, SN RPMDA662, installed. This AD requires stripping of thermal spray coating, inspection of dovetail slots, and reapplication of thermal spray coating on certain stage 1 fan disks.



DOCUMENT.

Airworthiness directives, Grob-Werke GMBH & Co. KG G102 CLUB ASTIR III,

G102 CLUB ASTIR IIIb, and G102 STANDARD ASTIR III gliders: Airworthiness

Directives; GROB-WERKE GMBH & CO KG Models G102 CLUB ASTIR III, G102 CLUB

ASTIR IIIb, and G102 STANDARD ASTIR III Gliders, Federal Register, November 29,


Docket No. FAA-2007-28670 Directorate Identifier 2007-CE-060-AD, Amendment

39-15277, AD 2007-24-11, RIN 2120-AA64, Final rule.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective January 3, 2008. On January 3, 2008 the Director of the Federal Register approves the incorporation by reference of certain publications listed in this AD.)


SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for GROB-

WERKE GMBH & CO KG Models G102 CLUB ASTIR III, G102 CLUB ASTIR IIIb, and

G102 STANDARD ASTIR III gliders. This AD results from mandatory continuing airworthiness information (MCAI) issued 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:

GROB received isolated difficulty reports regarding cracks on welded parts of the flight control system of the type G102, model CLUB ASTIR III & IIIb, and

STANDARD ASTIR III. The cracks progress slowly from the welding seams periphery, and may eventually result in rupture at a matured stage.



DOCUMENT.

Airworthiness directives, Hartzell Propeller Inc. HC-E5N-3( ), HC-E5N-

3()(L), and HC-E5B-5( ) propellers: Airworthiness Directives; Hartzell Propeller

Inc. Model HC-E5N-3( ), HC-E5N-3( )(L), and HC-E5B-5( ) Propellers, Federal

Register, November 29, 2007, Volume 72, Number 229, Rules and Regulations, Page

67564, 14 CFR Part 39, Docket No. FAA-2007-28656, Directorate Identifier 2007-NE-

31-AD, Amendment 39-15280, AD 2007-24-14, RIN 2120-AA64, Final rule, request for comments.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective December 14, 2007. The Director of the Federal Register approves the incorporation by reference of certain publications listed in the regulations as of December 14, 2007. The Federal Aviation

Administration (FAA) must receive any comments on this AD by January 28, 2008.)

PURPOSE: This airworthiness directive (AD) results from the discovery of a fivebladed propeller hub with a large crack on the mounting flange of the hub in certain

Hartzell Propeller Inc. Model HC-E5N-3( ), HC-E5N-3( )(L), and HC-E5B-5( ) propellers. This AD requires actions intended to prevent propeller hub failure, blade separation, damage to the airplane, and possible loss of airplane control.

SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for Hartzell

Propeller Inc. Model HC-E5N-3( ), HC-E5N-3( )(L), and HC-E5B-5( ) propellers. This

AD requires a onetime eddy current inspection of the propeller hub mounting bolt holes and replacement of the propeller hub if cracked.



DOCUMENT.

Airworthiness directives, Hartzell Propeller Inc. Compact Series Propellers:

Airworthiness Directives; Hartzell Propeller Inc. Compact Series Propellers, Federal



08-AD, Amendment 39-15311, AD 2007-26-09, RIN 2120-AA64, Final rule.

[TEXT] [PDF]


Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of June 13, 2002 (67 FR 31113, May 9,

2002). The Director of the Federal Register approves the incorporation by reference of certain publications listed in the regulations as of January 30, 2008.)

PURPOSE: This airworthiness directive (AD) results from operators requesting clarification of certain parts of AD 2002-09-08. This AD requires actions intended to prevent failure of the propeller blade from fatigue cracks in the blade shank radius, which can result in damage to the airplane and loss of airplane control.

SUMMARY: The Federal Aviation Administration (FAA) supersedes an existing AD for all Hartzell Propeller Inc. models ( )HC-( )( )Y( )-( )( )( ) compact series, constant speed or feathering propellers with Hartzell manufactured “Y” shank aluminum blades. That AD currently requires initial blade inspections, with no repetitive inspections; rework of all “Y” shank aluminum blades including cold rolling of the blade shank retention radius, blade replacement and modification of pitch change mechanisms for certain propeller models; and changing the airplane operating limitations with specific models of propellers installed. This AD requires the same actions but clarifies certain areas of the compliance, and updates a certain service bulletin (SB) reference to the most recent SB.



DOCUMENT.

Airworthiness directives, Hawker Beechcraft 400A series: Airworthiness

Directives; Hawker Beechcraft Model 400A Series Airplanes, Federal Register,




[TEXT] [PDF]



PURPOSE: This airworthiness directive (AD) results from reports of undersized, and consequently unprotected, wire in the galley cabinets in certain Hawker Beechcraft

Model 400A series airplanes. This AD requires actions intended to prevent overheating of wire insulation and consequent fire or smoke in the airplane cabin.


Hawker Beechcraft Model 400A series airplanes. This AD requires inspecting the galley cabinets to determine if a certain part number is installed or if a certain size of wire already exists, and doing related investigative/corrective actions if necessary.



DOCUMENT.

Airworthiness directives, McDonnell Douglas DC-9-81 (MD-81) and DC-9-82

(MD-82): Airworthiness Directives; McDonnell Douglas Model DC-9-81 (MD-81) and

DC-9-82 (MD-82) Airplanes, Federal Register, December 10, 2007, Volume 72,



2007-25-16, RIN 2120-AA64, Final rule.

[TEXT] [PDF]



PURPOSE: This airworthiness directive (AD) results from reports of fatigue cracking in the fuselage skin at the upper corners of the forward passenger doorjamb of certain McDonnell Douglas Model DC-9-81 (MD-81) and DC-9-82 (MD-82) airplanes.

This AD requires actions intended to prevent cracking of the fuselage skin at the upper corners of the forward passenger doorjamb, which could lead to loss of overall structural integrity of the airplane.


McDonnell Douglas Model DC-9-81 (MD-81) and DC-9-82 (MD-82) airplanes. This AD requires, for certain airplanes, inspecting for cracking of the fuselage skin at the upper corners of the forward passenger doorjamb, installing or replacing doublers as applicable, and doing applicable repairs.



DOCUMENT.

Airworthiness directives, McDonnell Douglas DC-10-10, DC-10-10F, DC-10-

15, DC-10-30 and DC-10-30F (KC-10A and KDC-10); Model DC-10-40 and

DC-10-40F Airplanes; and Model MD-11 and MD-11F Airplanes: Airworthiness

Directives; McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30 and DC-10-30F (KC-10A and KDC-10) Airplanes; Model DC-10-40 and DC-10-40F

Airplanes; and Model MD-11 and MD-11F Airplanes, Federal Register, December 17,


Docket No. FAA-2005-21470, Directorate Identifier 2003-NM-45-AD, Amendment


[TEXT] [PDF]


Federal Register approves the incorporation by reference of certain publications listed in the AD as of January 22, 2008. On October 1, 2001 (66 FR 44950, August 27,

2001), the Director of the Federal Register approved the incorporation by reference of McDonnell Douglas Service Bulletin DC10-78-060, dated December 17, 1999. On

April 25, 2001 (66 FR 15785, March 21, 2001), the Director of the Federal Register approved the incorporation by reference of McDonnell Douglas Alert Service Bulletin

DC10-78A057, Revision 01, dated February 18, 1999.)

PURPOSE: This airworthiness directive (AD) results from a determination that the thrust reverser systems on these McDonnell Douglas airplanes do not adequately preclude unwanted deployment of a thrust reverser. This AD requires actions intended to prevent an unwanted deployment of a thrust reverser during flight, which could result in reduced controllability of the airplane.


McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30 and DC-10-

30F (KC-10A and KDC-10) airplanes; Model DC-10-40 and DC-10-40F airplanes; and

Model MD-11 and MD-11F airplanes. This AD requires, for certain airplanes, modifying the thrust reverser command wiring of the number 2 engine. For certain other airplanes, this AD requires modifying the thrust reverser system wiring from the flight compartment to engines 1, 2, and 3 thrust reversers. This AD also requires installing thrust reverser locking systems on certain airplanes.



DOCUMENT.

Airworthiness directives, MT-Propeller Entwicklung GmH: Airworthiness

Directives; MT-Propeller Entwicklung GmbH Propellers, Federal Register, December


39, Docket No. FAA-2005-20856, Directorate Identifier 2004-NE-25-AD, Amendment


[TEXT] [PDF]

(This airworthiness directive (AD) is effective January 31, 2008.)

PURPOSE: This airworthiness directive (AD) requires actions intended to prevent erosion sheath separation leading to damage of the airplane.

SUMMARY: The Federal Aviation Administration (FAA) supersedes an existing AD for certain MT-Propeller Entwicklung GmbH variable pitch and fixed pitch propellers manufactured before 1995, which had not been overhauled since April 1994. That AD currently requires overhauling the propeller blades and performing initial and repetitive visual inspections of affected propeller blades. That AD also requires removing all propeller blades from service with damaged erosion sheath bonding or loose erosion sheaths and installing any missing or damaged polyurethane protective strips. This AD requires the same actions. This AD results from the need to clarify the affected propellers previously listed in AD 2006-05-05.



DOCUMENT.

Airworthiness directives, Piaggio Aero Industries: Airworthiness Directives;

Piaggio Aero Industries S.p.A. Model P-180 Airplanes, Federal Register, December 3,


Docket No. FAA-2007-27532 Directorate Identifier 2007-CE-021-AD, Amendment

39-15281, AD 2007-24-15, RIN 2120-AA64, Final Rule.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective January 7, 2008. As of January 7, 2008 the Director of the Federal Register approves the incorporation by reference of certain publications listed in this AD.)


SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for Piaggio

Aero Industries S.p.A. Model P-180 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product.


One P 180 aircraft experienced a jamming of its longitudinal flight control cables. Investigations revealed that its fuselage drain holes were plugged, and water was trapped in the lower fuselage.

As a consequence of plugged drain holes, water can accumulate and freeze when the aircraft reaches and holds altitudes where temperature is below the freezing point. If not corrected this may cause the loss of control of the airplane.



DOCUMENT.

Airworthiness directives, Reims Aviation S.A. F406: Airworthiness Directives;

REIMS AVIATION S.A. Model F406 Airplanes, Federal Register, December 27, 2007,

Volume 72, Number 247, Rules and Regulations, Page 73258, 14 CFR Part 39,

Docket No. FAA-2007-0115 Directorate Identifier 2007-CE-080-AD, Amendment 39-

15310, AD 2007-26-08, RIN 2120-AA64, Final rule.

[TEXT] [PDF]




SUMMARY: The Federal Aviation Administration (FAA) adopts a new AD for REIMS

AVIATION S.A. Model F406 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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:

On several occasions, leaks of the landing gear emergency blowdown bottle have been reported. Investigations revealed that the leakage was

located on the nut manometer because of a design deficiency in the bottle head.

If left uncorrected, the internal bottle pressure could not be maintained to an adequate level and could result in a malfunction, failing to extend landing gears during emergency situations.



DOCUMENT.

Airworthiness directives, Rolls-Royce Corp. AE 3007A and AE 3007C series

turbofan engines: Airworthiness Directives; Rolls-Royce Corporation AE 3007A and

AE 3007C Series Turbofan Engines, Federal Register, November 28, 2007, Volume

72, Number 228, Rules and Regulations, Page 67242, 14 CFR Part 39, Docket No.

FAA-2007-26966, Directorate Identifier 99-NE-01-AD, Amendment 39-15271, AD

2007-24-05, RIN 2120-AA64, Final rule.

[TEXT] [PDF]


Federal Register approves the incorporation by reference of certain publications listed in the regulations as of January 2, 2008.)

PURPOSE: This airworthiness directive (AD) results from design improvements to components in the accessory gearbox air turbine starter mounting pad in certain AE

3007A and AE 3007C series turbofan engines. This AD requires actions intended to prevent an in-flight engine shutdown due to loss of engine oil from the engine accessory gearbox starter pad shaft seal drain and possible loss of the airplane.

SUMMARY: The Federal Aviation Administration (FAA) supersedes an existing airworthiness directive (AD) for Rolls-Royce Corporation (RRC) AE 3007A and AE

3007C series turbofan engines. That AD currently prohibits any flight following a ground engine start where the engine oil temperature is below 32˚F (0˚C), unless certain preflight operational procedures are followed. This AD requires those actions and also requires an action, which, when taken allows other procedures to be avoided (terminating action).



DOCUMENT.

Airworthiness directives, Rolls-Royce plc RB211 Trent 768-60, 772-60, and

772B-60 turbofan engines: Airworthiness Directives; Rolls-Royce plc, RB211 Trent

768-60, 772-60, and 772B-60 Turbofan Engines, Federal Register, November 29,


Docket No. FAA-2006-26052, Directorate Identifier 2006-NE-30-AD, Amendment 39-

15275, AD 2007-24-09, RIN 2120-AA64, Final rule, request for comments.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective December 14, 2007. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of December 19, 2006 (71 FR 66229,

November 14, 2006). The Director of the Federal Register approves the incorporation

by reference of certain publications listed in the regulations as of December 14,

2007. The Federal Aviation Administration (FAA) must receive any comments on this

AD by January 28, 2008.)

PURPOSE: This airworthiness directive (AD) results from RR introducing a revised

HP/IP turbine bearing support structure as terminating action to the repetitive inspections of the HP/IP turbine bearing oil feed tube heat shield in Rolls-Royce plc

(RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD requires actions intended to prevent an uncontained failure of the HP turbine disc and damage to the airplane.

SUMMARY: The Federal Aviation Administration (FAA) supersedes an existing AD for

Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines.

That AD currently requires initial and repetitive on-wing or in-shop inspections of the high pressure/intermediate pressure (HP/IP) turbine bearing oil feed tube heat shield. This AD requires the same actions but introduces a terminating action to the repetitive inspections.



DOCUMENT.

Airworthiness directives, Societe de Motorisations Aeronautiques SR305-

230 and SR305-230-1 reciprocating engines: Airworthiness Directives; Societe de Motorisations Aeronautiques (SMA) SR305-230 and SR305-230-1 Reciprocating

Engines, Federal Register, November 28, 2007, Volume 72, Number 228, Rules and


Identifier 2006-NE-36-AD, Amendment 39-15272, AD 2007-24-06, RIN 2120-AA64,

Final rule, request for comments.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective December 13, 2007. The Director of the Federal Register approves the incorporation by reference of SMA Service

Bulletin (SB) No. SB-01-76-005, dated December 15, 2006, as of December 13,

2007. The Federal Aviation Administration (FAA) must receive any comments on this

AD by December 28, 2007.)

PURPOSE: This airworthiness directive (AD) requires actions intended to prevent a rapid uncontrolled power increase and possible loss of control of the airplane.

SUMMARY: The Federal Aviation Administration (FAA) supersedes an existing AD for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) provided by the European Aviation Safety Agency (EASA) to identify and correct an unsafe condition on SMA SR305-230 and SR305-230-1 reciprocating engines. The MCAI states the following:

Over a period of time, the alteration of one electronic control unit (ECU) electronic component can cause a rapid uncontrolled power increase. Several occurrences have already been reported during engine start or during engine warm-up. This condition, if not corrected, could result in the loss of control of the aircraft if the pilot fails to react appropriately by switching to the mechanical backup mode.



DOCUMENT.

Airworthiness directives, Thrush Aircraft, Inc.: Airworthiness Directives; Thrush

Aircraft, Inc. Model S2R Series Airplanes, Federal Register, December 17, 2007,


Docket No. FAA-2007-28432, Directorate Identifier 2007-CE-051-AD, Amendment


[TEXT] [PDF]



PURPOSE: This airworthiness directive (AD) results from reports of cracks in the empennage of Thrush S2R series airplanes. This AD requires actions intended to detect and correct these cracks, which could cause the vertical stabilizer to lose structural integrity. This failure could lead to loss of control.


Thrush Aircraft, Inc. (Thrush) Model S2R series airplanes. This AD requires you to do repetitive visual inspections of the vertical and horizontal stabilizer attach fitting, attach fitting bolts, and the vertical fin aft spar for cracks or corrosion. This AD also requires immediate replacement of the vertical and horizontal stabilizer attach fittings and attach fitting bolts if cracked or corroded parts are found, and the inspection of the vertical fin aft spar with repair or replacement if cracks or corrosion are found. If no corrosion or cracks are found, this AD requires the replacement of the vertical and horizontal stabilizer attach fittings and attach fitting bolts, within the next 2,000 hours time in service after January 22, 2008, or the next two years after

January 22, whichever occurs first. This replacement allows you to stop performing the repetitive inspections.



DOCUMENT.

Airworthiness directives, Turbomeca Arriel 2S1 and 2S2 turboshaft engines:

Airworthiness Directives; Turbomeca Arriel 2S1 and 2S2 Turboshaft Engines, Federal

Register, November 29, 2007, Volume 72, Number 229, Rules and Regulations, Page


17-AD, Amendment 39-15276, AD 2007-24-10, RIN 2120-AA64, Final rule, request for comments.

[TEXT] [PDF]

(This airworthiness directive (AD) is effective December 14, 2007. The Director of the Federal Register approves the incorporation by reference of Turbomeca, S.A.

Mandatory Service Bulletin No. 292 73 2824, dated February 1, 2007, listed in the

AD as of December 14, 2007. The Federal Aviation Administration (FAA) must receive any comments on this AD by December 31, 2007.)

PURPOSE: This airworthiness directive (AD) requires actions intended to prevent a fuel leak as a result of a ruptured fuel filter drain screw that could lead to engine flame-out or an engine fire.

SUMMARY: The FAA adopts a new airworthiness directive (AD) for the Turbomeca

Arriel 2S1 and 2S2 Turboshaft Engines. This AD results from mandatory continuing airworthiness information (MCAI) provided by the European Aviation Safety Agency

(EASA) to identify and correct an unsafe condition on the engines. The MCAI states the following:

During assembly of a new HP/LP fuel pump, the drain screw on the fuel filter unit failed when it was tightened to the torque value specified in the assembly schedule (12 Nm). Investigation of the screw showed that it was fully conformed to its specification, in terms of both dimensions and material. The mechanical calculations show, however, that a torque value of 12 Nm is too high for this screw, exceeding the elastic limit of the material. Failure of the affected screw could cause a fuel leak, resulting in an engine flame-out or engine fire.



DOCUMENT.

Airworthiness standards, damage tolerance data for repairs and alterations:

Damage Tolerance Data for Repairs and Alterations, Federal Register, December 12,

2007, Volume 72, Number 238, Rules and Regulations, Page 70486, 14 CFR Parts

26, 121, and 129, Docket No. FAA-2005-21693, Amendment Nos. 26-1, 121-337,

129-44, RIN 2120-AI32, Final rule.

[TEXT] [PDF]

(This final rule is effective January 11, 2008.)

SUMMARY: This action requires holders of design approvals to make available to operators damage tolerance data for repairs and alterations to fatigue critical airplane structure. This rule supports operator compliance with the Aging Airplane

Safety final rule with respect to the requirement to incorporate into the maintenance program, a means for addressing the adverse effects repairs and alterations may have on fatigue critical structure. The intent of this final rule is to ensure the continued airworthiness of fatigue critical airplane structure by requiring design approval holders to support operator compliance with specified damage tolerance requirements.

Airworthiness standards, normal, utility, acrobatic, and commuter category

airplanes, emergency landing conditions, CFR correction: Airworthiness

Standards: Normal, Utility, Acrobatic, and Commuter Category Airplanes, Federal


72915, 14 CFR Part 23, CFR correction.

[TEXT] [PDF]

CORRECTION: In Title 14 of the Code of Federal Regulations, Parts 1 to 59, revised as of January 1, 2007, on page 227, in Section 23.561, five paragraphs beginning with the second paragraph (d)(1)(i) through paragraph (d)(1)(v) are removed.

Airworthiness standards, special conditions, ASPEN Avionics Inc. EFD 1000:

Special Conditions; ASPEN Avionics Inc. Model EFD 1000; Electronic Flight

Instrument System (EFIS); Protection of Systems for High Intensity Radiated Fields

(HIRF), Federal Register, December 10, 2007, Volume 72, Number 236, Rules and

Regulations, Page 69579, 14 CFR Part 23, Docket No. CE278, Special Condition 23-

218-SC, Final special conditions, request for comments.

[TEXT] [PDF]

(These final special conditions are effective November 30, 2007. Any public comments must be received on or before January 9, 2008.)

SUMMARY: These special conditions are issued to ASPEN Avionics Inc., for a

Supplemental Type Certificate for the models listed under the heading “Type

Certification Basis” under the Approved Model List Process. These airplanes have novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. These novel and unusual design features include the installation of electronic flight instrument system (EFIS) displays

Model EFD 1000 manufactured by ASPEN Avionics Inc., for which 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.



DOCUMENT.

Airworthiness standards, special conditions, Bell Helicopter Textron Canada

Ltd. Model 429 helicopters: Special Condition: Bell Helicopter Textron Canada

Limited Model 429 Helicopters, High Intensity Radiated Fields, Federal Register,


14 CFR Parts 21 and 27, Docket No. SW017, Special Condition No. 27-017-SC, Final special condition, request for comments.

[TEXT] [PDF]

(This final special condition is effective December 11, 2007. Any public comments must be received on or before February 11, 2008.)

SUMMARY: This special condition is issued for the Bell Helicopter Model 429 helicopters. These helicopters have novel or unusual design features associated with installing electrical and electronic systems that perform critical functions, including an Electronic Flight Instrument System (EFIS) and a Full Authority Digital Engine

Control (FADEC). The applicable airworthiness regulations do not contain adequate or appropriate safety standards to protect systems that perform critical control functions, or provide critical displays, from the effects of high-intensity radiated fields (HIRF). This special condition contains the additional safety standards that the

Administrator considers necessary to ensure that critical functions of systems are maintained when exposed to HIRF.



DOCUMENT.

Airworthiness standards, special conditions, Boeing Model 757 series

airplanes: Special Conditions: Boeing Model 757 Series Airplanes; Seats With Non-

Traditional, Large, Non-Metallic Panels, Federal Register, December 28, 2007,


Docket No. NM385, Special Conditions No. 25-364-SC, Final special conditions.

[TEXT] [PDF]

(These special conditions are effective December 18, 2007.)

SUMMARY: These special conditions are issued for Boeing Model 757 Series

Airplanes. These airplanes, as modified by Triad International Maintenance Company

(TIMCO), have a novel or unusual design feature(s) associated with seats that include non-traditional, large, non-metallic panels that affect survivability during a post-crash fire. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These 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.



DOCUMENT.

Airworthiness standards, special conditions, Boeing Model 787-8 airplane:

Special Conditions: Boeing Model 787-8 Airplane; Systems and Data Networks

Security-Protection of Airplane Systems and Data Networks from Unauthorized

External Access, Federal Register, December 28, 2007, Volume 72, Number 248,

Rules and Regulations, Page 73582, 14 CFR Part 25, Docket No. NM365 Special

Conditions No. 25-357-SC, Final special conditions.

[TEXT] [PDF]

(These final special conditions are effective January 28, 2008.)

SUMMARY: These special conditions are issued for the Boeing Model 787-8 airplane.

This airplane has novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. The architecture of the Boeing Model 787-8 computer systems and networks may allow access to external systems and networks, such as wireless airline operations and maintenance systems, satellite communications, electronic mail, the Internet, etc. On-board wired and wireless devices may also have access to parts of the airplane's digital systems that provide flight critical functions. These new connectivity capabilities may result in security vulnerabilities to the airplane's critical systems. For these design features, the applicable airworthiness regulations do not contain adequate or appropriate safety standards for protection and security of airplane systems and data networks against unauthorized access. These 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

standards. Additional special conditions will be issued for other novel or unusual design features of the Boeing Model 787-8 airplanes.



DOCUMENT.

Airworthiness standards, special conditions, ASPEN Avionics Inc. EFD 1000:

Special Conditions; ASPEN Avionics Inc. Model EFD 1000; Electronic Flight

Instrument System (EFIS); Protection of Systems for High Intensity Radiated Fields

(HIRF), Federal Register, December 10, 2007, Volume 72, Number 236, Rules and



[TEXT] [PDF]


SUMMARY: These special conditions are issued to ASPEN Avionics Inc., for a

Supplemental Type Certificate for the models listed under the heading “Type

Certification Basis” under the Approved Model List Process. These airplanes have novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. These novel and unusual design features include the installation of electronic flight instrument system (EFIS) displays

Model EFD 1000 manufactured by ASPEN Avionics Inc., for which 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.



DOCUMENT.

Airworthiness standards, special conditions, Cirrus Design Corp. SR22:

Special Conditions; L-3 Communications Avionics Systems Model SmartDeck in

Cirrus Design Corporation Model SR22; Installation of Electronic Flight Instrument

System (EFIS); Protection of Systems for High Intensity Radiated Fields (HIRF),




[TEXT] [PDF]


SUMMARY: These special conditions are issued to L-3 Communications Avionics

Systems, for a Supplemental Type Certificate for the Cirrus Design Corporation Model

SR22. This airplane has novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. These novel and unusual design features include the installation of electronic flight instrument system (EFIS) displays Model SmartDeck manufactured by L-3 Communications

Avionics Systems for which 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.



DOCUMENT.

Airworthiness standards, special conditions, Honda Aircraft Co., HA-420

Hondajet: Special Conditions; Honda Aircraft Company Model HA-420 Hondajet;

Protection of Systems for High Intensity Radiated Fields (HIRF), Federal Register,


14 CFR Part 23, Docket No. CE277, Special Condition 23-217-SC, Final special conditions, request for comments.

[TEXT] [PDF]


SUMMARY: These special conditions are issued to Honda Aircraft Company, for a

Type Certificate for the HA-420 Hondajet airplane. This airplane has novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. These novel and unusual design features include the installation of electronic flight instrument system (EFIS) displays Model G1000 manufactured by Garmin for which 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.



DOCUMENT.

Airworthiness standards, special conditions, Pilatus Aircraft Ltd.

PC/12/47E: Special Conditions; Pilatus Aircraft Ltd.; Model PC-12/47E; Protection of Systems for High Intensity Radiated Fields (HIRF), Federal Register, December 10,


Docket No. CE276, Special Condition 23-216-SC, Final special conditions, request for comments.

[TEXT] [PDF]


SUMMARY: These special conditions are issued to Pilatus Aircraft Ltd., for an

Amended Type Certificate for the Model PC-12/47E airplane. This airplane has novel and unusual design features when compared to the state of technology envisaged in

the applicable airworthiness standards. These novel and unusual design features include the installation of electronic flight instrument system (EFIS) displays

Model APEX manufactured by Honeywell for which 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.



DOCUMENT.

Class D and E airspace, Easton, MD: Establishment of Class D and E Airspace,

Revision of Class E Airspace; Easton, MD, Federal Register, December 13, 2007,


Docket No. FAA-2007-28601, Airspace Docket No. 07-AEA-02, Final rule.

[TEXT] [PDF]

(This final rule is effective 0901 UTC, February 14, 2008. The Director of the

Federal Register approves this incorporation by reference action under title 1, Code of Federal Regulations, Part 51, subject to the annual revision of Federal Aviation

Administration (FAA) Order 7400.9 and publication of conforming amendments.)

SUMMARY: This action establishes Class D, E2 and E4 airspace at Easton, MD to provide adequate airspace to support the new Air Traffic Control Tower constructed at Easton Airport/Newnam Field. This action provides controlled airspace for

Instrument Approaches and Instrument and Visual Flight Rule operations to increase safety and airspace management. This action also amends Class E5 airspace at

Easton, MD by correcting the airport's name.



DOCUMENT.

Class D and Class E airspace, Kenai, AK: Revision of Class D and E Airspace;

Kenai, AK, Federal Register, December 19, 2007, Volume 72, Number 243, Rules and

Regulations, Page 71757, 14 CFR Part 71, Docket No. FAA-2007-29011, Airspace

Docket No. 07-AAL-14, Final rule.

[TEXT] [PDF]

(This final rule is effective 0901 UTC, February 14, 2008. The Director of the Federal

Register approves this incorporation by reference action under Title 1, Code of

Federal Regulations, Part 51, subject to the annual revision of Federal Aviation


SUMMARY: This action revises Class D and E airspace at Kenai, AK to provide adequate controlled airspace to contain aircraft executing Standard Instrument

Approach Procedures (SIAPs). Five SIAPs are amended for the Kenai Municipal

Airport at Kenai, AK. Additionally, one textual departure procedure (DP) is amended.

This action revises existing Class D and E airspace upward from the surface, from

700 feet (ft.) and 1,200 ft. above the surface at the Kenai Municipal Airport,

Kenai, AK.



DOCUMENT.

Class E airspace, Buckland, AK: Revision of Class E Airspace; Buckland, AK,




[TEXT] [PDF]





SUMMARY: This action revises Class E airspace at Buckland, AK to provide adequate controlled airspace to contain aircraft executing Standard Instrument Approach

Procedures (SIAPs). Two SIAPs and a textual departure procedure (DP) are amended for the Buckland Airport. Additionally, two SIAPs are being developed. This action revises existing Class E airspace upward from 700 feet (ft.) and 1,200 ft. above the surface at the Buckland Airport, Buckland, AK.



DOCUMENT.

Class E airspace, Chevak, AK: Revision of Class E Airspace; Chevak, AK, Federal


71764, 14 CFR Part 71, Docket No. FAA-2007-29010, Airspace Docket No. 07-AAL-

13, Final rule.

[TEXT] [PDF]





SUMMARY: This action revises Class E airspace at Chevak, AK to provide adequate controlled airspace to contain aircraft executing Standard Instrument Approach

Procedures (SIAPs). Two SIAPs are developed for the Chevak Airport. This action revises existing Class E airspace upward from 700 feet (ft.) and 1,200 ft. above the surface at the Chevak Airport, Chevak, AK.



DOCUMENT.

Class E airspace, Farmington, ME: Establishment of Class E Airspace; Farmington,

ME, Federal Register, December 19, 2007, Volume 72, Number 243, Rules and


Docket No. 07-ANE-93, Direct final rule, request for comments.

[TEXT] [PDF]

(This direct final rule is effective 0901 UTC, February 14, 2008. The Director of the

Federal Register approves this incorporation by reference action under Title 1, Code of Federal Regulations, Part 51, subject to the annual revision of Federal Aviation

Administration (FAA) Order 7400.9 and publication of conforming amendments. Any public comments for inclusion in the Rules Docket must be received February 4,

2008.)

SUMMARY: This action establishes additional Class E Airspace at Farmington, ME.

The existing controlled airspace does not adequately support a new Area Navigation

(RNAV) Global Positioning System (GPS) Special Instrument Approach Procedure

(IAP) that has been developed for medical flight operations. This action enhances the safety and management of Instrument Flight Rule (IFR) operations by providing the required controlled airspace to protect for this approach around Franklin Memorial

Hospital.



DOCUMENT.

Class E airspace, Honesdale, PA: Establishment of Class E Airspace; Honesdale,

PA, Federal Register, December 13, 2007, Volume 72, Number 239, Rules and


Docket No. 07-AEA-12, Direct final rule, request for comments.

[TEXT] [PDF]



Administration (FAA) Order 7400.9 and publication of conforming amendments. Any public comments for inclusion in the Rules Docket must be received on or before

January 10, 2008.)

SUMMARY: This action establishes additional Class E Airspace at Honesdale, PA. The existing controlled airspace does not adequately support a new Area Navigation

(RNAV) Global Positioning System (GPS) Special Instrument Approach Procedure

(IAP) that has been developed for medical flight operations. This action enhances the safety and management of Instrument Flight Rule (IFR) operations by providing the required controlled airspace to protect for this approach around Honesdale, PA.



DOCUMENT.

Class E airspace, Lewiston, ME: Establishment of Class E Airspace; Lewiston, ME,




[TEXT] [PDF]



Administration (FAA) Order 7400.9 and publication of conforming amendments.

Any public comments for inclusion in the Rules Docket must be received on or before

February 4, 2008.)

SUMMARY: This action establishes Class E Airspace at Lewiston, ME. The existing controlled airspace from nearby Auburn/Lewiston Municipal Airport does not adequately support a new Area Navigation (RNAV) Global Positioning system (GPS)

Special Instrument Approach Procedure (IAP) that has been developed for medical flight operations. This action enhances the safety and management of Instrument

Flight Rule (IFR) operations by providing the required controlled airspace to protect for this approach around the Central Maine Medical Center.



DOCUMENT.

Class E airspace, McGrath, AK: Revision of Class E Airspace; McGrath, AK, Federal



15, Final rule.

[TEXT] [PDF]





SUMMARY: This action revises Class E airspace at McGrath, AK to provide adequate controlled airspace to contain aircraft executing Standard Instrument Approach

Procedures (SIAPs). Five SIAPs and a textual departure procedure (DP) are being amended for the McGrath Airport. Additionally, one SIAP is being developed. This action revises existing Class E airspace upward from 700 feet (ft.) and 1,200 ft. above the surface at the McGrath Airport, McGrath, AK.



DOCUMENT.

Class E airspace, Montrose, PA: Establishment of Class E Airspace; Montrose, PA,




[TEXT] [PDF]




January 28, 2008.)

SUMMARY: This action establishes Class E Airspace near the High School at

Montrose, PA. Controlled airspace 700 feet above the surface of the Earth is required to support a new Area Navigation (RNAV) Global Positioning System (GPS) Special

Instrument Approach Procedure (IAP) that has been developed for medical flight operations. This action enhances the safety and management of Instrument Flight

Rule (IFR) operations by providing the required controlled airspace to protect for this approach at Montrose, PA.



DOCUMENT.

Class E airspace, Oil City, PA: Establishment of Class E Airspace; Oil City, PA.,




[TEXT] [PDF]


Federal Register approves this incorporation by reference action under Title, Code of



February 4, 2008.)

SUMMARY: This action establishes Class E Airspace at Oil City, PA to provide adequate airspace for a new Area Navigation (RNAV) Global Positioning System

(GPS) Special Instrument Approach Procedure (IAP) that has been developed to serve the Northwest Medical Center (PS42). This action enhances the safety and management of Instrument Flight Rule (IFR) operations at Oil City, PA.



DOCUMENT.

Class E airspace, Prairie Du Sac, WI: Establishment of Class E5 Airspace; Prairie

Du Sac, WI, Federal Register, December 14, 2007, Volume 72, Number 240, Rules and Regulations, Page 71060, 14 CFR Part 71, Docket No. FAA-2007-28778, Airspace

Docket No. 07-AGL-6, Final rule.

[TEXT] [PDF]


Register approves this incorporation by reference action under 1 CFR Part 51, subject to the annual revision of Federal Aviation Administration (FAA) Order 7400.9 and publication of conforming amendments.)

SUMMARY: This rule establishes a Class E airspace area extending upward from 700 feet above the surface at Prairie Du Sac, WI. This rule provides appropriate controlled Class E airspace for aircraft departing from and executing instrument approach procedures to Sauk-Prairie Airport, Prairie du Sac, WI and segregates aircraft using instrument approach procedures in instrument conditions from aircraft operating in visual conditions.



DOCUMENT.

Class E airspace, Selawik, AK: Revision of Class E Airspace; Selawik, AK, Federal



05, Final rule.

[TEXT] [PDF]





SUMMARY: This action revises Class E airspace at Selawik, AK to provide adequate controlled airspace to contain aircraft executing Standard Instrument Approach

Procedures (SIAPs). Two SIAPs are amended for the Selawik Airport. This action revises existing Class E airspace upward from 700 feet (ft.) and 1,200 ft. above the surface at the Selawik Airport, Selawik, AK.



DOCUMENT.

Class E airspace, Skowhegan, ME: Establishment of Class E Airspace; Skowhegan,

ME, Federal Register, December 19, 2007, Volume 72, Number 243, Rules and



[TEXT] [PDF]




February 4, 2008.)

SUMMARY: This action establishes Class E Airspace at Skowhegan, ME. The existing controlled airspace from nearby Central Maine Airport does not adequately support a new Area Navigation (RNAV) Global Positioning System (GPS) Special Instrument

Approach Procedure (IAP) that has been developed for medical flight operations. This action enhances the safety and management of Instrument Flight Rule (IFR) operations by providing the required controlled airspace to protect for this approach around the Redington-Fairview General Hospital in Skowhegan.



DOCUMENT.

Class E airspace, Soldotna, AK: Revision of Class E Airspace; Soldotna, AK,




[TEXT] [PDF]

(This final rule is effective 0901 UTC, February 14, 2008. The Director of the



SUMMARY: This action revises Class E airspace at Soldotna, AK to provide adequate controlled airspace to contain aircraft executing Standard Instrument Approach

Procedures (SIAPs). Two SIAPs are being developed for the Soldotna Airport. This action revises existing Class E airspace upward from 700 feet (ft.) and 1,200 ft. above the surface at the Soldotna Airport, Soldotna, AK.



DOCUMENT.

IFR altitudes: IFR Altitudes; Miscellaneous Amendments, Federal Register,


14 CFR Part 95, Docket No. 30582, Amendment No. 471, Final rule.

[TEXT] [PDF]

(This final rule is effective 0901 UTC, December 20, 2007.)

SUMMARY: This action adopts miscellaneous amendments to the required IFR

(instrument flight rules) altitudes and changeover points for certain federal airways, jet routes, or direct routes for which a minimum or maximum en route authorized

IFR altitude is prescribed. This regulatory action is needed because of changes occurring in the National Airspace System. These changes are designed to provide for the safe and efficient use of the navigable airspace under instrument conditions in the affected areas.



DOCUMENT.

Practice and procedure, rulemaking petitions, information requirements,

CFR correction: General Rulemaking Procedures, Federal Register, December 28,


CFR Correction.

[TEXT] [PDF]

CORRECTION: In Title 14 of the Code of Federal Regulations, Parts 1 to 59, revised as of January 1, 2007, on page 27, Section 11.71 is reinstated to read as follows:

Section 11.71 What information must I include in my petition for rulemaking?

(a) You must include the following information in your petition for rulemaking:

(1) Your name and mailing address and, if you wish, other contact information such as a fax number, telephone number, or e-mail address.

(2) An explanation of your proposed action and its purpose.

(3) The language you propose for a new or amended rule, or the language you would remove from a current rule.

(4) An explanation of why your proposed action would be in the public interest.

(5) Information and arguments that support your proposed action, including relevant technical and scientific data available to you.

(6) Any specific facts or circumstances that support or demonstrate the need for the action you propose.

(b) In the process of considering your petition, we may ask that you provide information or data available to you about the following:

(1) The costs and benefits of your proposed action to society in general and identifiable groups within society in particular.

(2) The regulatory burden of your proposed action on small businesses, small organizations, small governmental jurisdictions, and

Indian tribes.

(3) The recordkeeping and reporting burdens of your proposed action and whom the burdens would affect.

(4) The effect of your proposed action on the quality of the natural and social environments.



DOCUMENT.

Organization, functions, and authority delegations, Transportation

Department address change and migration to Federal Docket Management

System: Change in Address for the Department of Transportation (DOT) and DOT

Migration to the Federal Docket Management System (FDMS), Federal Register,

December 5, 2007, Volume 72, Number 233, Rules and Regulations, Page 68473, 14

CFR Parts 11, 13, 17, 36, 91, 139, 150, 193, 404, and 406, Final rule, technical amendment.

[TEXT] [PDF]

(This final rule, technical amendment, is effective December 5, 2007.)

SUMMARY: This action updates the Department of Transportation (DOT) addresses, changes references from the Docket Management System to the Federal Docket

Management System (FDMS), and removes obsolete information listed in the Federal

Aviation Administration (FAA) regulations as a result of the DOT's relocation, migration to the Federal electronic docket system, and closure of the DOT Branch

Library. This action is to ensure that the regulated public is informed of address changes, electronic docket changes, and other administrative matters.



DOCUMENT.

Standard instrument approach procedures: Standard Instrument Approach

Procedures; Miscellaneous Amendments, Federal Register, November 28, 2007,


Docket No. 30581, Amendment No. 3246, Final rule.

[TEXT] [PDF]

(This final rule is effective November 28, 2007. The compliance date for each

Standard Instrument Approach Procedure (SIAP) is specified in the amendments.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 28, 2007.)

SUMMARY: This action amends Standard Instrument Approach Procedures (SIAPs) for operations at certain airports. These regulatory actions are needed because of changes in the National Airspace System, such as the commissioning of new navigational facilities, adding of new obstacles, or changing air traffic requirements.

These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.



DOCUMENT.


Procedures, and Takeoff Minimums and Obstacle Departure Procedures;

Miscellaneous Amendments, Federal Register, December 4, 2007, Volume 72,

Number 232, Rules and Regulations, Page 68062, 14 CFR Part 97, Docket No.

30580, Amdt. No. 3245, Final rule.

[TEXT] [PDF]

(This final rule is effective December 4, 2007. The compliance date for each

Standard Instrument Approach Procedure (SIAP), associated Takeoff Minimums, and

Obstacle Departure Procedure (ODP) is specified in the amendments. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 4, 2007.)

SUMMARY: This action establishes, amends, suspends, or revokes Standard

Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and

Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.



DOCUMENT.


Procedures; Miscellaneous Amendments, Federal Register, December 13, 2007,


Docket No. 30584, Amdt. No. 3248, Final rule.

[TEXT] [PDF]


Standard Instrument Approach Procedure (SIAP) is specified in the amendments.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 13, 2007.)

SUMMARY: This action amends Standard Instrument Approach Procedures (SIAPs) for operations at certain airports. These regulatory actions are because of changes in the National Airspace System, such as the commissioning of new navigational facilities, adding of new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.



DOCUMENT.






[TEXT] [PDF]



Obstacle Departure Procedures (ODPs) is specified in the amendments. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 13, 2007.)



Obstacle Departure Procedures (ODPs) for operations at certain airports. These regulatory actions are because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.



DOCUMENT.






[TEXT] [PDF]



Obstacle Departure Procedure (ODP) is specified in the amendments. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 31, 2007.)



Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.



DOCUMENT.

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FEDERAL HIGHWAY ADMINISTRATION (FHWA)

Engineering and traffic operations, temporary traffic control devices, work

zone safety protection measures for workers and motorists: Temporary Traffic

Control Devices, Federal Register, December 5, 2007, Volume 72, Number 233,

Rules and Regulations, Page 68480, 23 CFR Part 630, FHWA Docket No. FHWA-2006-

25203, RIN 2125-AF10, Final rule.

[TEXT] [PDF]

(This final rule is effective December 4, 2008. The incorporation by reference of certain publications listed in this rule is approved by the Director of the Federal

Register as of December 4, 2008.)

SUMMARY: The Federal Highway Administration (FHWA) adds a new Subpart K to 23

CFR Part 630 to supplement existing regulations for work zone safety and mobility in highway and street work zones to include conditions for the appropriate use of, and expenditure of funds for, uniformed law enforcement officers, positive protective measures between workers and motorized traffic, and installation and maintenance of temporary traffic control devices during construction, utility, and maintenance operations. These regulations are to decrease the likelihood of deaths and injuries to road users, and to workers who are exposed to traffic while working on Federal-aid highway projects. The regulations are issued in accordance with section 1110 of the

Safe, Accountable, Flexible, Efficient Transportation Equity Act: A Legacy for Users

(SAFETEA-LU), Public Law 109-59, 119 Stat. 1227, codified at 23 U.S.C. 109(e) and

112(g).



DOCUMENT.

Engineering and traffic operations, Uniform Traffic Control Devices Manual,

traffic sign retroreflectivity, maintenance methods: National Standards for

Traffic Control Devices; the Manual on Uniform Traffic Control Devices for Streets

and Highways; Maintaining Traffic Sign Retroreflectivity, Federal Register, December


655, FHWA Docket No. FHWA-2003-15149, RIN 2125-AE98, Final rule.

[TEXT] [PDF]

(This final rule is effective January 22, 2008. The incorporation by reference of the publication listed in this regulation is approved by the Director of the Office of the

Federal Register as of January 22, 2008.)

SUMMARY: The Manual on Uniform Traffic Control Devices (MUTCD) is incorporated by reference in 23 CFR Part 655, subpart F, approved by the Federal Highway

Administration (FHWA), and recognized as the national standard for traffic control devices used on all public roads. This final rule revises standards, guidance, options, and supporting information relating to maintaining minimum levels of retroreflectivity for traffic signs on all roads open to public travel. A “retroreflective” surface bounces light back to a source of light, in this case, allowing a driver to read a sign when the car’s headlights hit it.



DOCUMENT.

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FEDERAL RAILROAD ADMINISTRATION (FRA)

Alcohol and drug testing, minimum random testing rates determination:

Alcohol and Drug Testing: Determination of Minimum Random Testing Rates for

2008, Federal Register, December 31, 2007, Volume 72, Number 249, Rules and

Regulations, Page 74193, 49 CFR Part 219, Docket No. 2001-11213, Notice No. 11,

RIN 2130-AA81, Notice of Determination.

[TEXT] [PDF]

(This determination is effective upon publication.)

SUMMARY: Using data from Management Information System annual reports,

The Federal Railroad Administration (FRA) determines that the 2006 rail industry random testing positive rates were 0.60 percent for drugs and 0.13 percent for alcohol. Because the industry-wide random drug testing positive rate has remained below 1.0 percent for the last two years, the Federal Railroad Administrator

(Administrator) determines that the minimum annual random drug testing rate for the period January 1, 2008, through December 31, 2008, remains at 25 percent of covered railroad employees. In addition, because the industry-wide random alcohol testing violation rate has remained below 0.5 percent for the last two years, the

Administrator determines that the minimum random alcohol testing rate remains at

10 percent of covered railroad employees for the period January 1, 2008, through

December 31, 2008.

Railroad accidents/incidents, reports classifications and investigations,

monetary threshold (2008 CY): Adjustment of Monetary Threshold for Reporting

Rail Equipment Accidents/Incidents for Calendar Year 2008, Federal Register,


49 CFR Part 225, FRA-2007-0018, Final rule.

[TEXT] [PDF]


SUMMARY: This action increases the rail equipment accident/incident reporting threshold from $8,200 to $8,500 for certain railroad accidents/incidents involving property damage that occur during calendar year 2008. This action is to ensure that the Federal Railroad Administration's (FRA’s) reporting requirements reflect cost increases that have occurred since the reporting threshold was last computed for calendar year 2007.

----------------

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FEDERAL MOTOR CARRIER SAFETY ADMINISTRATION (FMCSA)

Motor carrier safety standards, drivers’ hours of service, on-duty driving

time adjustments: Hours of Service of Drivers, Federal Register, December 17,

2007, Volume 72, Number 241, Rules and Regulations, Page 71247, 49 CFR Parts

385 and 395, Docket No. FMCSA-2004-19608, RIN-2126-AB14, Interim final rule

(IFR), request for comments.

[TEXT] [PDF]

(This interim final rule (IFR) is effective December 27, 2007. Any public comments must be received on or before February 15, 2008.)

PURPOSE: The procedures surrounding a regulation are being revisited in response to a ruling by the United States Court of Appeals for the District of Columbia Circuit.

This interim final rule keeps the current regulation in effect while everything is sorted out.

SUMMARY: The Federal Motor Carrier Safety Administration (FMCSA) amends the

Federal Motor Carrier Safety Regulations effective December 27 to allow commercial motor vehicle (CMV) drivers up to 11 hours of driving time within a 14-hour, nonextendable window from the start of the workday, following 10 consecutive hours off duty (“11-hour limit”). This interim rule also allows motor carriers and drivers to restart calculations of the weekly on-duty time limits after the driver has at least 34 consecutive hours off duty (“34-hour restart”). This IFR is to ensure that a familiar and uniform set of national rules governs motor carrier transportation, while the

FMCSA gathers public comments on all aspects of this interim final rule, conducts peer review of the FMCSA’s analysis, and considers the appropriate final rule that addresses the issues identified by the Court. The FMCSA commits to issuing a final rule in 2008.

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FEDERAL TRANSIT ADMINISTRATION (FTA)

National transit database uniform system of accounts and reporting system,

Nonurbanized Area Formula Grant recipients, reporting requirements, etc.:

National Transit Database: Amendment to Reporting Requirements and Non-

Substantive Technical Changes, Federal Register, December 6, 2007, Volume 72,

Number 234, Rules and Regulations, Page 68756, 49 CFR Part 630, Docket No: FTA-

2007-27319, RIN 2132-AA94, Final rule.

[TEXT] [PDF]


SUMMARY: This notice announces the final rule requiring recipients of grants under

49 U.S.C. 5311, Formula Grants for Other Than Urbanized Areas (Nonurbanized Area

Formula Grants,) to report annual data to the National Transit Database (NTD) as a condition for receiving these grants. In addition, this final rule makes nonsubstantive changes, technical corrections, and conforming amendments to the

“National Transit Database” regulation.

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NATIONAL HIGHWAY TRAFFIC SAFETY ADMINISTRATION (NHTSA)

Motor vehicle safety standards, lamps, reflective devices and associated

equipment: Federal Motor Vehicle Safety Standards; Lamps, Reflective Devices, and

Associated Equipment, Federal Register, December 4, 2007, Volume 72, Number

232, Rules and Regulations, Page 68233, Part II, 49 CFR Parts 564 and 571, Docket

No. NHTSA-2007-28322, RIN 2127-AJ75, Final Rule.

[TEXT] [PDF]

(This final rule is effective September 1, 2008 with voluntary early compliance permitted immediately. The incorporation by reference of certain publications listed in the rule is approved by the Director of the Federal Register as of September 1,

2008. Any petitions for reconsideration of this final rule must be received not later than January 18, 2008.)

SUMMARY: This action amends the Federal Motor Vehicle Safety Standard (FMVSS)

No. 108 on lamps, reflective devices, and associated equipment by reorganizing the regulatory text so that it provides a more straightforward and logical presentation of the applicable regulatory requirements, which includes the agency's interpretation of the existing requirements. It also greatly reduces the need to consult relevant thirdparty standards by including applicable requirements directly into the main body of

Standard No. 108, rather than incorporating such provisions by reference. This final rule does not impose any new substantive requirements on manufacturers.

In addition, this document amends 49 CFR Part 564, Replaceable Light Source

Information, by adding a newly created Appendix C, which relocates figures addressing sealed beam headlamps that currently reside in FMVSS No. 108 and a relevant Society of Automotive Engineers (SAE) standard there. The National

Highway Traffic Safety Administration (NHTSA) believes few lighting manufacturers still produce sealed beam headlamps, and their diminishing use is unlikely to draw new manufacturers of this type of lamp. Accordingly, the NHTSA sees no drawbacks to consolidating the information regarding sealed beam light sources with other light source information currently located in 49 CFR Part 564.

Motor vehicle safety standards, motor homes and recreation vehicle trailers

over 10,000 pounds, cargo carrying capacity, tire selection and rims: Federal

Motor Vehicle Safety Standards; Cargo Carrying Capacity, Federal Register,


Part III, 49 CFR Part 571, DOT Docket No. NHTSA-2007-0040, RIN 2127-AJ57, Final rule.

[TEXT] [PDF]

(This final rule is effective June 2, 2008. Optional immediate compliance is available as of December 4, 2007. Any petitions for reconsideration of the final rule must be received not later than January 18, 2008.)

SUMMARY: In this action, the National Highway Traffic Safety Administration

(NHTSA) addresses the problem of motor home and recreation vehicle trailer overloading by amending the Federal Motor Vehicle Safety Standards (FMVSS) on tire selection and rims.

This final rule requires manufacturers of all motor homes and recreation vehicle trailers to provide information to consumers in a label that informs the consumer about the vehicle's load carrying capacity. This information is helpful both at the time the consumer is making a purchase decision and as the consumer uses his or her vehicle. The NHTSA also requires that the size of tires on motor homes and recreation vehicle trailers be the same as the size of the tires listed on the tire information label.

In addition, this rule provides regulatory relief for dealers from a labeling requirement in the safety standard on tire selection and rims for light vehicles. The standard's requirement can currently require dealers which add even small amounts of weight to re-label the vehicles. Under today's amendment, any party that adds weight to a completed vehicle exceeding the lesser of 1.5 percent of the vehicle's gross vehicle weight rating or 100 pounds (before first sale to the retail customer) is required to disclose this extra weight on labels affixed to the vehicles. Lesser amounts of weight may be added without changing or adding labels.

The NHTSA believes that this rule complements the efforts of the recreation vehicle industry to provide consumers with information in order to help reduce overloading motor homes and recreation vehicle trailers. This rulemaking was initiated in response to a petition from Ms. Justine May.

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PIPELINE AND HAZARDOUS MATERIALS SAFETY ADMINISTRATION (PHMSA)

Pipeline safety, gas distribution operators, public awareness regulations

applicability: Pipeline Safety: Applicability of Public Awareness Regulations to

Certain Gas Distribution Operators, Federal Register, December 13, 2007, Volume

72, Number 239, Rules and Regulations, Page 70808, 49 CFR Part 192, Docket ID

PHMSA-2003-15852, RIN 2137-AE17, Final rule.

[TEXT] [PDF]


SUMMARY: This action relaxes regulatory requirements for public awareness programs conducted by operators of master meter systems and certain operators of petroleum gas systems. These operators typically manage property and incidentally provide gas service to customers located on the property. The change provides a less burdensome means for these operators to satisfy public awareness needs.



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