FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2005-08 This electronic copy may be printed and used in lieu of the FAA biweekly paper copy.
U.S. Department of Transportation Federal Aviation Administration Regulatory Support Division Delegation and Airworthiness Programs Branch, AIR-140 P. O. Box 26460 Oklahoma City, OK 73125-0460 FAX 405-954-4104
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SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No.
Information
Manufacturer
Applicability
Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2005-01 2004-26-09
2004-26-11 2005-01-04
2005-01-10 2005-01-11
Rolls-Royce Corporation
S 98-15-13
S 74-06-01
Bell Helicopter Textron Canada Raytheon Aircraft Company
The New Piper Aircraft, Inc Pilatus Aircraft Ltd.
Engine: 250-B17, -B17B, -B17C, -B17D, -B17E, 250-C20, -C20B, -C20F, -C20J, -C20S, and -C20W Series Turboprop and Turboshaft Rotorcraft: 222, 222B, 222U, 230, 430 65-90, 65-A90, B90, C90, C90A, C90B, E90, F90, H90, 100, A100, A100-1, (RU-21J), B100, 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, B300C, 99, 99A, A99,, A99A, B99, C99 PA-23-235, PA-23-250, and PA-E23-250 PC-12 and PC-12/45
Biweekly 2005-02 98-20-38 R1
R
Raytheon Aircraft Company
2005-01-14 2005-01-17 2005-01-18
S 2002-21-16 S 98-03-14 S 93-25-07
Bombardier-Rotax GmbH EXTRA Flugzeugbau GmbH Raytheon Aircraft Company
2005-01-19
S 2004-10-15
GARMIN International Inc
2005-02-01
The Lancair Company
Beech 200 (A100-1 (U-21J)), Beech 200C, Beech 200CT, Beech 200T, Beech A200 (C-12A) or (C-12C), Beech A200C (UC-12B), Beech A200CT (C-12D), (FWC-12D), (RC-12D), (C-12F), (RC-12G), (RC-12H), (RC-12K), or (RC-12P), B200CT, and B200T Engine: 912 F, 912 S, and 914 F Series Reciprocating EA–300 and EA–300/S A100–1 (U–21J), 200, B200, A200 (C–12A), A200 (C–12C), A200C (UC–12B), A200CT (C–12D), A200CT (FWC–12D), A200CT (RC–12D), A200CT (C–12F), A200CT (RC–12G), A200CT (RC–12H), A200CT (RC–12K), A200CT (RC–12P), A200CT (RC–12K), 200C, B200C, 200CT, 200T, B200C (C-12F), B200C (UC–12F), B200C (UC–12M), B200CT, 300, B300, B300C, and B300C Appliance: GTX 33, GTX 33D, GTX 330, and GTX 330D Mode S Transponders LC40–550FG and LC42–550FG
Biweekly 2005-03 2005-01-04
COR S 98-15-13
Raytheon Aircraft Company
2005-01-18
COR S 93-25-07
Raytheon Aircraft Company
2005-02-11 2005-03-04
COR
Gippsland Aeronautics Pty. Ltd. Pacific Aerospace Corp., Ltd.
65–90, 65–A90, B90, C90, C90A, E90, F90, H90, 100, A100, A100–1 (RU–21J), B100, 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, B300C, 99, 99A, A99, A99A, B99, and C99 A100–1 (U–21J), 200, B200, A200 (C–12A), A200 (C–12C), A200C (UC–12B), A200CT (C–12D), A200CT (FWC–12D), A200CT (RC–12D), A200CT (C–12F), A200CT (RC–12G), A200CT (RC–12H), A200CT (RC–12K), A200CT (RC–12P), A200CT (RC–12K), 200C, B200C, 200CT, B200CT, 200T, B200T, B200C (C–12F), B200C (UC–12F), B200C (UC–12M), B200CT, 300, B300C, and B300C GA8 750XL
Biweekly 2005-04 2005-01-04
COR S 98-15-13
2005-03-07 2005-03-08 2005-03-09
2005-03-10 2005-04-09
Raytheon Aircraft Company
Bell Helicopter Textron Canada Eurocopter France Eurocopter France
S 2002-08-54 S 2004-26-11
Bell Helicopter Textron Bell Helicopter Textron Canada
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65–90, 65–A90, B90, C90, C90A, E90, F90, H90, 100, A100, A100–1 (RU–21J), B100, 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, B300C, 99, 99A, A99, A99A, B99, C99 Rotorcraft: 407 Rotorcraft: AS350B, BA, B1, B2, B3, C, D, D1, and EC130 B4 Rotorcraft: EC 155B, EC155B1, SA-360C, SA-365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 Rotorcraft: 222, 222B, 222U, and 230 Rotorcraft: 222, 222B, 222U, 230, and 430
SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No.
Information
Manufacturer
Applicability
Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2005-05 2005-04-08 2005-04-10 2005-04-16 2005-05-51 2005-05-52 2005-05-53 2005-05-53 R1
Hartzell Propeller Inc. General Electric Company
E E, S 2005-05-51 E E, R, S 2005-0553
Propeller: HC-B3TN-5( )/T10282( ) Engine: CT58-140-1, CT58-140-2, and surplus military T58-GE-5, -10, -100, and ''402 turboshaft PC-12 and PC-12/45 402C and 414A 402C and 414A 172R, 172S, 182T, and T182T 172R, 172S, 182T, and T182T
Pilatus Aircraft Ltd. Cessna Aircraft Company Cessna Aircraft Company Cessna Aircraft Company Cessna Aircraft Company
Biweekly 2005-06 2005-05-14 2005-05-15
Eagle Aircraft (Malaysia) Honeywell International Inc.
2005-06-01
Eurocopter France
Eagle 150B Engine: TFE731-2 and -2C series, and TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series turbofan Rotorcraft: EC 155B and EC 155B1
Cessna
402C and 414A
Cessna Fairchild Aircraft, Inc.
172R, 172S, 182T, and T182T SA226-AT, SA226-TC, SA226-T, SA226-T(B), SA227-TT, SA227-TT(300), SA227-AC, SA227-AT, SA227-BC, and SA227CC/DC 208 and 208B
Biweekly 2005-07 2005-05-52 2005-05-53 R1 2005-06-13
FR, S 2005-05-51 and 2000-23-01 R, 2005-05-53 S 99-0602
2005-07-01
Cessna
Biweekly 2005-08 83-08-01 R2
R, S 83-08-01 R1
Hartzell Propeller Inc.
2005-07-01 2005-07-27
COR S 2000-18-04
Cessna Aviointeriors S.p.A.
Propeller: HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, and HC-B5MP-3 turbopropellers 208 and 208B Appliance: Model 312 Seats
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BW 2005-08 HARTZELL PROPELLER INC. AIRWORTHINESS DIRECTIVE REVISION SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
83-08-01R2 Hartzell Propeller Inc. (formerly TRW Hartzell Propeller): Amendment 39-14043. Docket No. 83-ANE-14-AD. Revises AD 83-08-01R1, Amendment 39-4633 Applicability This AD is applicable to Hartzell Propeller Inc. (formerly TRW Hartzell Propeller) models HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, and HC-B5MP-3 turbopropellers. The HC-B()TN-2, HC-B()TN-3, and HC-B()MP-3 propellers are typically installed on Pratt & Whitney Canada Model PT6A-() series engines. The HC-B()TN-5 and HC-B()MN-5 series propellers are typically installed on Honeywell International Inc., (formerly AlliedSignal Inc., Garrett Turbine Engine Company, and AIResearch Manufacturing Company of Arizona) TPE-331-() series engines. Note 1: This AD applies to each propeller identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For propellers that have been modified, altered, or repaired so that the performance of the requirements of this AD are affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance Compliance with this AD is required as indicated, unless already done. To preclude propeller attaching bolt failures or improperly secured propellers, which could lead to separation of the propeller from the airplane, do the following: (a) Install all new propellers and serviceable propellers, as follows, before further flight: (1) Install the propeller oil seal to the engine flange after ensuring that the engine and propeller flanges are clean. (2) Carefully install propeller on the engine flange ensuring that complete and true contact is established. (3) Apply MIL-T-83483 Petrolated Graphite, or Hartzell Lubricant part number (P/N) A3338, to threads of the eight P/N B-3339 attaching bolts (and remainder of bolt if desired) and to flat surfaces of the eight P/N A-2048-2 washers, or to other equivalent FAA-approved serviceable bolts and washers. (4) Install the eight P/N B-3339 attaching bolts and eight P/N A-2048-2 washers, or other equivalent FAA-approved serviceable bolts and washers, that were prepared in paragraph (a)(3) of this AD, through the engine flange and into the propeller flange.
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83-08-01 R2 2
(5) Torque all attaching bolts with a torque wrench and an appropriate adapter, to 40 ft.-lbs., and then to 80 ft.-lbs., following sequence ''A'' (shown below). Final torque all attaching bolts using sequence ''B'' (shown below) to 100 ft.-lbs. to 105 ft.-lbs. Safety wire all attaching bolts in an FAAapproved manner.
(6) Once the propeller is installed with P/N B-3339 bolts and P/N A-2048-2 washers, or other equivalent FAA-approved serviceable bolts and washers, this AD no longer applies. (b) Within the next 300 hours time-in-service after the effective date of this AD, do the following on all applicable turbopropellers presently installed with P/N A-2047 attaching bolts: (1) Check the torque, with a torque wrench and an appropriate adapter, of all eight propeller attaching bolts (with washers installed). Torque should be 100 ft-lbs. to 125 ft.-lbs., with dry threads. (Caution: Do not use any lubricant with the P/N A-2047 bolts. Safety wire all bolts in an FAAapproved manner.) (2) If the torque of any one of the bolts is found to be less than 100 ft.-lbs., remove all eight bolts and washers and replace with P/N B-3339 bolts and P/N A-2048-2 washers, or other equivalent FAA-approved serviceable bolts and washers, using paragraphs (a)(1) through (a)(5) of this AD. (3) A P/N A-2047 bolt has the letter ''H'' stamped inside a triangle on the bolt. A P/N B-3339 bolt has the P/N stamped inside the cupped head. (4) If the torque of each P/N A-2047 bolt is in compliance, then at next propeller disassembly, remove all eight bolts and washers and replace with P/N B-3339 bolts and P/N A-2048-2 washers, or other equivalent FAA-approved serviceable bolts and washers. Use paragraphs (a)(1) through (a)(5) of this AD to do the replacements. (5) Hartzell Service Instructions No. 140A, Revision 9, dated March 30, 2005, is the latest service information that pertains to the subject of this AD. Alternative Methods of Compliance (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Chicago Aircraft Certification Office. Operators must submit their requests through an appropriate FAA Principal Maintenance 6
83-08-01 R2 3
Inspector, who may add comments and then send it to the Manager, Chicago Aircraft Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Chicago Aircraft Certification Office. Special Flight Permits (d) Special flight permits may be issued in accordance with §§ 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be done. Effective Date (e) This amendment becomes effective on May 11, 2005. Issued in Burlington, Massachusetts, on March 30, 2005. Diane Cook, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-6778 Filed 4-5-05; 8:45 am] BILLING CODE 4910-13-P
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BW 2005-08 THE CESSNA AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
CORRECTION: [Federal Register: April 8, 2005 (Volume 70, Number 67); Page 17889; www.access.gpo.gov/su_docs/aces/aces140.html] 2005-07-01 The Cessna Aircraft Company: Amendment 39-14025; Docket No. FAA-2005-20514; Directorate Identifier 2005-CE-08-AD. When Does This AD Become Effective? (a) This AD becomes effective on March 29, 2005. Are Any Other ADs Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Models 208 and 208B, all serial numbers, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD results from several accidents/incidents of problems with the affected airplanes during operations in icing condition, including six accidents in the previous two icing seasons and nine events in the past few months. We are issuing this AD to assure that the pilot has enough information to prevent loss of control of the airplane while in-flight during icing conditions. What Must I Do To Address This Problem? (e) No later than April 1, 2005 (3 days after March 29, 2005, which is the effective date of this AD), incorporate the following revisions into the Airplane Flight Manual:
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2005-07-01 2
Affected airplanes
Incorporate the following AFM revision Revise the Performance Section document (Section 5) of the AFM Supplement by inserting the fol-lowing text (this may be done by inserting a copy of this AD in the AFM Supplement) None. (1) Cessna Model 208 Section 2: Limitations and Section 4: airplanes and Model 208B Normal Procedures: Temporary Revision 208PHTR04, dated March 2, 2005, to the airplanes, all serial Pilots Operating Handbook (POH) and FAAnumbers. approved Airplane Flight Manual (AFM), except replace the Limitations (Section 2) of the Temporary Revision 208PHTR04 to the POH/FAA-approved AFM with the Appendix to this AD. (This may be done by inserting a copy of this AD into the POH/AFM.). (2) Cessna Model 208 Section 9: Optional Systems Description and WARNING: The stall warning system has not been tested in all Operating Procedures: Revision 5 of the airplanes with a Pratt & icing conditions and should not be 208 (675 SHP) POH/FAA-approved AFM Whitney of Canada Ltd., Supplement S1 ‘‘Known Icing Equipment’’ relied upon in icing conditions. PT6A–114A turboprop engine installed (675 SHP) Cessna document D1352–S1–05, dated or FAA-approved engine of March 2, 2005. equivalent horsepower installed, except airplanes modified by Supplemental Type Certificate SA0892WI. (3) Cessna Model 208 Section 9: Optional Systems Description and WARNING: The stall warning system has not been tested in all Operating Procedures Revision 5 of the airplanes with a Pratt & icing conditions and should not be Cessna Model 208 (600 SHP) POH/FAAWhitney of Canada Ltd., relied upon in icing conditions. approved AFM Supplement S1 ‘‘Known PT6A–114 turboprop engine installed (600 SHP) Icing Equipment’’, Cessna document or FAA-approved engine of D1307–S1–05, dated March 2, 2005, except incorporate the Appendix to this AD into equivalent horsepower installed, except airplanes paragraphs ‘‘PREFLIGHT’’and modified by Supplemental ‘‘VISUAL/TACTILE CHECK’’of the Limitations Section of the POH/FAAType Certificate approved AFM Supplement S1 ‘‘Known SA00892WI. Icing Equipment’’. (4) Cessna Model 208B Section 9: Optional Systems Description and WARNING: The stall warning system has not been tested in all Operating Procedures Revision 6 of the airplanes with a Pratt & 208B (675 SHP) POH/FAA-approved AFM icing conditions and should not be Whitney of Canada Ltd., Supplement S1 ‘‘Known Icing Equipment’’, relied upon in icing conditions. PT6A–114A turboprop engine installed (675 SHP) Cessna document D1329–S1–06, dated or FAA-approved engine of March 2, 2005. equivalent horsepower installed, except airplanes modified by Supplemental Type Certificate SA00892WI. 9
2005-07-01 3
(5) Cessna Model 208B airplanes with a Pratt & Whitney of Canada Ltd., PT6A–114A turboprop engine installed (600 SHP) or FAA-approved engine of equivalent horsepower installed, except airplanes modified by Supplemental Type Certificate SA00892WI.
Section 9: Optional Systems Description and Operating Procedures Revision 5 of the 208B (600 SHP) POH/FAA-approved AFM Supplement S1 ‘‘Known Icing Equipment’’, Cessna document D1309– S1–05, dated March 2, 2005.
WARNING: The stall warning system has not been tested in all icing conditions and should not be relied upon in icing conditions.
(f) The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do the flight manual changes requirement of this AD. Make an entry in the aircraft records showing compliance with this portion of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). May I Request an Alternative Method of Compliance? (g) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Staff, Small Airplane Directorate, FAA, c/o Paul Pellicano, Aerospace Engineer (Icing), FAA, Small Airplane Directorate, c/o Atlanta Aircraft Certification Office (ACO), One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, GA 30349; telephone: (770) 703-6064; facsimile: (770) 703-6097. For information on any already approved alternative methods of compliance, contact Paul Pellicano at the address and phone number above. May I Get Copies of the Document Referenced in this AD? (h) You may obtain the service information referenced in this AD from The Cessna Aircraft Company, Product Support, PO Box 7706, Wichita, Kansas 67277-7706; telephone: (316) 517-5800; facsimile: (316) 942-9006. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC, or on the Internet at http://dms.dot.gov. This is docket number FAA-2005-20048; Directorate Identifier 2005-CE-08-AD. Appendix to AD 2005-07-01, Amendment 39-14025 [Docket No. FAA-2005-20514; Directorate Identifier 2005-CE-08-AD] Preflight Takeoff is prohibited with any frost, ice, snow, or slush adhering to the wings, horizontal stabilizer, control surfaces, propeller blades, and engine inlets.
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Warning Even small amounts of frost, ice, and snow, or slush on the wing may adversely change lift and drag. Failure to remove these contaminants will degrade airplane performance and may prevent a safe takeoff and climbout. Visual/Tactile Check In addition to a visual check, a tactile check of the wing leading edge, wing upper surface (up to two feet behind the deicing boot at on-span location as a minimum), horizontal tail leading edge, and propeller blades is required if the outside air temperature (OAT) is below 5° C (41° F) and visible moisture (rain, drizzle, sleet, snow, fog etc.) is present or the airplane was exposed to visible moisture (rain, drizzle, sleet, snow, fog etc.) since the previous landing; or the airplane experienced in-flight ice accretion since the previous takeoff; or the difference between the dew point temperature and the OAT is 3° C (5° F) or less; or water is present on the wing. Reference the preflight procedures in Section 4 of the basic Pilot's Operating Handbook. Issued in Kansas City, Missouri, on March 21, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-5915 Filed 3-24-05; 8:45 am] BILLING CODE 4910-13-P
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BW 2005-08 AVIOINTERIORS S.P.A. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
2005-07-27 Aviointeriors S.p.A. (formerly ALVEN): Amendment 39-14052. Docket No. 2000NE-09-AD. Effective Date (a) This AD becomes effective May 16, 2005. Affected ADs (b) This AD supersedes AD 2000-18-04. Applicability (c) This AD applies to Aviointeriors S.p.A. (formerly ALVEN), model 312 seats. These seats are installed in, but not limited to, Fokker Model F27 Mark 050, Mark 500, and Mark 600 airplanes. Unsafe Condition (d) This AD results from reports of 88 cracked seat central crossmembers and 60 aisle side crossmembers, to date; and, from the introduction of reinforced optional seat crossmembers by the manufacturer. The actions specified in this AD are intended to prevent the loss of the structural integrity of the seat due to cracks in seat crossmembers, which could lead to passenger injury. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Initial Visual Inspection (f) Perform an initial visual inspection of the crossmember for cracks, within 12,000 hours time-in-service (TIS); or within 180 days after the effective date of this AD if the crossmember has more than 12,000 hours TIS, as follows: (1) Inspect seat central crossmembers, part number (P/N) DM03437-1, using Section 2. of Inspection Procedure of Aviointeriors Service Bulletin (SB) No. 312/912-01, Revision 2, dated August 1, 2000. (2) Replace any cracked central crossmember with a new crossmember of the same P/N. Use Section 3. Crossmember Replacement Procedure, Steps 3.1 though 3.10 of Aviointeriors SB No. 312/912-01, Revision 2, dated August 1, 2000.
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(3) Inspect seat aisle side crossmembers, P/Ns DM03435-1, DM03435-2, and DM03437-1 (Disabled People seat application), using Section 2. of Inspection Procedure of Aviointeriors SB No. 312/912-02, Revision 1, dated August 1, 2000. (4) Replace any cracked aisle side crossmember with a new crossmember of the same P/N. Use Section 3. Crossmember Replacement Procedure, Steps 3.1 though 3.8 of Aviointeriors SB No. 312/912-02, Revision 1, dated August 1, 2000. Repetitive Visual Inspections (g) Perform repetitive visual inspections of crossmembers, P/N DM03435-1, DM03435-2, and DM03437-1, for cracks, within 650 hours TIS after the last inspection. Use paragraphs (f)(1) through (f)(4) of this AD to inspect and disposition crossmembers. Optional Terminating Action (h) As optional terminating actions to the repetitive inspections required by this AD, do the following: (1) Replace seat central crossmembers, P/N DM03437-1, with reinforced crossmembers, P/N F11541300000. Use Section 2. Crossmember Replacement Procedure, Steps 2.1 through 2.11 of Aviointeriors SB No. 312/912-03, dated August 1, 2000. (2) Replace seat aisle side crossmembers, P/N DM03435-1, DM03435-2, and DM03437-1 (Disabled People seat application), with reinforced crossmembers, P/N F11555400000, F11555500000, and F11541300000, respectively. Use Section 2. Crossmember Replacement Procedure, Steps 2.1 through 2.11 of Aviointeriors SB No. 312/912-04, dated August 1, 2000. Alternative Methods of Compliance (i) The Manager, Boston Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (j) You must use the Aviointeriors service information specified in Table 1 of this AD to perform the inspections and replacements required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents in Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Aviointeriors S.p.A., Via Appia Km. 66.4–04013 Latina, Italy; telephone: 39-0773-6891; fax: 39-0773-631546, for a copy of this service information. You can review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Table 1 follows: TABLE 1.—INCORPORATION BY REFERENCE Aviointeriors service bulletin No. Page Revision Date 312/912–01, Total Pages: 8 ALL 2 August 1, 2000. 312/912–02, Total Pages: 9 ALL 1 August 1, 2000. 312/912–03, Total Pages: 8 ALL Original August 1, 2000. 312/912–04, Total Pages: 8 ALL Original August 1, 2000.
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Related Information (k) Ente Nazionale per l'Aviazione Civile airworthiness directives 2000-511 and 2000-512, both dated November 7, 2000, also address the subject of this AD. Issued in Burlington, Massachusetts, on April 1, 2005. Diane Cook, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-6912 Filed 4-8-05; 8:45 am] BILLING CODE 4910-13-P
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