Airworthiness Directives

Federal Regulation Brief
September 29, 2006

Today’s Brief Includes:
Transportation (DOT)—Federal Aviation
Administration (FAA) Airworthiness
Directives for Dangerous Conditions

TRANSPORTATION

NEWLY PUBLISHED REGULATIONS

FEDERAL AVIATION ADMINISTRATION (FAA)

AIRWORTHINESS DIRECTIVES (ADs) FOR UNSAFE CONDITIONS:
All ADs amend 14 CFR Section 39.13.

AD; Airbus Model A330, A340-200, and A340-300 Airplanes: Airworthiness Directives; Airbus Model A330, A340-200, and A340-300 Airplanes Federal Register: September 19, 2006 (Volume 71, Number 181, Rules and Regulations, page 54759-54761, 14 CFR Part 39, Docket No. FAA-2006-24793; Directorate Identifier 2006-NM-056-AD; Amendment 39-14764; AD 2006-19-07, RIN 2120-AA64, Final rule.
[TEXT]  [PDF]
(The effective date of this final rule is October 24, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 24, 2006, as well.)

PURPOSE: Some blow-down panels of the wing leading edges have fallen off while the plane was flying.

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330, A340-200, and A340-300 airplanes. This AD requires replacing the attachment landing assemblies of certain blow-down panels of the wing leading edges with new, improved landing assemblies.

AIRBUS MODEL A330, A340-200, AND A340-300: This document applies to the Airbus Model A330, A340-200, and A340-300 airplanes, certificated in any category; all serial numbers; except for airplanes which have received both Airbus Modification 47249 and Airbus Modification 53383 in production.

WITHIN 56 MONTHS OF OCTOBER 24, 2006, REPLACE THE LANDING ASSEMBLIES OF CERTAIN BLOW-DOWN PANELS OF THE WING LEADING EDGES WITH NEW, IMPROVED LANDING ASSEMBLIES, UNLESS THIS HAS ALREADY BEEN DONE: Use the service bulletins listed here to replace the landing assemblies:
FOR MODEL A330 AIRPLANES: Accomplishment Instructions of Airbus Service Bulletin A330-57-3091, dated October 25, 2005; or
FOR MODEL A340-200 AND A340-300 AIRPLANES: Airbus Service Bulletin A340-57-4100, dated October 25, 2005.
FOR THOSE PLANES THAT HAVE ALREADY BEEN FIXED: If, before Octobe 24, 2006, your plane has been fixed using the appropriate Service Bulletin applicable to your plane listed in Table 1, you are in compliance with the regulations.

Table 1.--Alternative Service Information
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Airbus Service Bulletin Revision # Effective date
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A330-57-3063....................... 01.................... July 23, 2004.
A330-57-3063....................... Original.............. July 12, 2001.
A330-57-3084....................... 01.................... February 17, 2006.
A330-57-3084....................... Original.............. December 14, 2004.
A340-57-4071....................... 02.................... September 10, 2004.
A340-57-4071....................... 01.................... July 23, 2004.
A340-57-4071....................... Original.............. July 12, 2001.
A340-57-4092....................... 01.................... February 17, 2006.
A340-57-4092....................... Original.............. December 14, 2004.
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ALTERNATIVE METHODS OF COMPLIANCE (AMOCS):
The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.
Before using any AMOC approved in accordance with Sec. 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office.

SERVICE BULLETINS: Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.


AD; Boeing Model 777-200 and -300 Series Airplanes: Airworthiness Directives; Boeing Model 777-200 and -300 Series Airplanes, Federal Register, September 25, 2006, Volume 71, Number 185, Rules and Regulations, page 55727-55729, 14 CFR Part 39, Docket No. FAA-2005-22874; Directorate Identifier 2005-NM-173-AD; Amendment 39-14769; AD 2006-19-12, RIN 2120-AA64, Final rule.
[TEXT]  [PDF]
(This AD is effective October 30, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of October 30, 2006.)

PURPOSE: Several discolored fairing lower webs and some damaged/deteriorated insulation blankets were found in the aft fairings of engine struts of certain Boeing Model 777-200 and -300 series airplanes. This AD is issued to prevent cracking of lower webs of the aft fairings, which could result in flammable hydraulic fluid leaking onto or near an ignition source, and possibly result in an uncontrollable fire in the engine strut area.

SUMMARY: Inspect the lower web of the aft fairing of engine struts for any discoloration and do any related investigative and corrective action if necessary; inspect the heat shield castings for any damage and do any corrective action if necessary; install gap cover strips; and replace insulation blankets with new insulation blankets.

BOEING MODEL 777-200 AND -300 SERIES AIRPLANES: This AD applies to Boeing Model 777-200 and -300 series airplanes, certificated in any category; as identified in Boeing Special Attention Service Bulletin 777-54-0021, Revision 1, dated March 16, 2006.

SERVICE BULLETIN: You must use Boeing Special Attention Service Bulletin 777-54-0021, Revision 1, dated March 16, 2006, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

BY OCTOBER 30, 2007: By October 30, 2007, in do the following actions using the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-54-0021, Revision 1, dated March 16, 2006.
Do a general visual inspection of the lower web of the aft fairing for any discoloration and do any related investigative action.
Do a general visual inspection of the heat shield castings for any damage (crack(s), dent(s), gouge(s), warpage, fretting, or missing/loose nutplates).
Install gap cover strips on the heat shield pans.
Replace insulation blankets on the heat shield pans with new insulation blankets.
IF ANY DAMAGE, DISCOLORATION, HEAT DAMAGE, OR CRACK IS FOUND DURING ANY INSPECTION REQUIRED BY THIS AD: Before further flight, do all applicable corrective actions in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, or in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-54-0021, Revision 1, dated March 16, 2006.

IF, BEFORE OCTOBER 30, 2006, YOU HAVE ALREADY FIXED YOUR AIRPLANE USING BOEING SPECIAL ATTENTION SERVICE BULLETIN 777-54-0021, DATED JUNE 23, 2005, THAT IS FINE, EXCEPT THAT THE SERVICE BULLETIN DOES NOT PROVIDE AN INTERNATIONAL ANNEALED COPPER STANDARD (ICAS) VALUE FOR DETERMINING THE RESULTS OF THE INSPECTION FOR HEAT DAMAGE: The maximum acceptable ICAS value is 42 percent.

CLARIFICATION OF SERVICE BULLETIN'S INCLUSION OF NUTPLATE INSPECTION; IF YOU FIND THE MISSING NUTPLATE EARLIER ON, IT SAVES TIME AND HASSLE: Service Bulletin 777-54-0021, Revision 1, includes in the general visual inspection for damage of the heat shield casting, a missing or loose nutplate as one criterion for damage. We consider this additional criterion a relieving action. Without the nutplate inspection in the general visual inspection for damage, a missing nutplate would be discovered during re-installation of the forward-most heat shield when fasteners would fail to be torqued to the correct torque value. Finding missing or loose nutplate(s) during the general visual inspection provides scheduling and economic benefits when compared to the cost of discovering missing nutplates after heat shield reinstallation.

CLARIFICATION OF ADDITIONAL AVAILABLE REPAIR METHOD: Service Bulletin 777-54-0021, Revision 1, also provides more detailed repair instructions that may be used for repair of conditions found during the inspections. We have revised Paragraph (g) of this AD to allow repair in accordance with the repair instructions provided by Service Bulletin 777-54-0021, Revision 1.

ALTERNATIVE METHODS OF COMPLIANCE (AMOCS):
The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.
Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office.
An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD.


AD; Cirrus Design Corporation Models SR20 and SR22 Airplanes: Airworthiness Directives; Cirrus Design Corporation Models SR20 and SR22 Airplanes, Federal Register, September 19, 2006, Volume 71, Number 181, Rules and Regulations, 54755-54757, 14 CFR Part 39, Docket No. FAA-2006-24254; Directorate Identifier 2006-CE-24-AD; Amendment 39-14767; AD 2006-19-10, RIN 2120-AA64, Final rule.
[TEXT]  [PDF]
(This AD is effective on October 24, 2006. As of October 24, 2006 the Director of the Federal Register approved the incorporation by reference of Cirrus Design Corporation Service Bulletin SB 2X-25-17 R1, Issued: December 15, 2005, Revised: January 20, 2006. As of October 13, 2005 (70 FR 51999, September 1, 2005), the Director of the Federal Register previously approved the incorporation by reference of Cirrus Design Corporation Service Bulletin SB 2X-25-06 R4, Issued: August 13, 2004; Revised: May 5, 2005.)

PURPOSE: AD 2005-17-19 currently requires you to measure and adjust the crew seat break-over bolts and to replace the crew seat recline locks on both crew seats in certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. Now there are new crew seat break-over pins to replace the old crew seat break-over bolts. Replacing the locks prevents the crew seats from folding forward during emergency landing dynamic loads, injuring crew members seated in them.

SUMMARY: Instead of using AD 2005-17-19, use this new one: 2006-19-10. You still have to replace the crew seat recline locks on both seats. You also now have to replace the crew seat break-over bolts with the new crew seat break-over pins on both seats.

WHICH MODELS SR20 AND SR22 AIRPLANES?: This AD affects Model SR20, Serial Numbers 1005 through 1600, and Model SR22, Serial Numbers 0002 through 1727, certificated in any category.

WITHIN 50 HOURS TIME-IN-SERVICE (TIS) OR WITHIN 180 DAYS: You must comply with this AD within 50 hours TIS or within 180 days, whichever occurs first, after the effective date of the AD you are required to follow, unless you have already done it. The AD you follow depends on the type of plane you have (please see the table of actions on 54756-54757 of the linked document). The table of actions also states exactly how to fix each type of plane according to the Cirrus Design Corporation Service Bulletins.

SERVICE BULLETINS: You must do the actions required by this AD following the instructions in Cirrus Design Corporation Service Bulletins SB 2X-25-17 R1, Issued: December 15, 2005, Revised: January 20, 2006; and SB 2X-25-06 R4, Issued: August 13, 2004; Revised: May 5, 2005. To get a copy of this service information, contact Cirrus Design Corporation, 4515 Taylor Circle, Duluth, Minnesota 55811;
telephone: (218) 727-2737; Internet address: http://www.cirrusdesign.com.
To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030.

ALTERNATIVE METHODS OF COMPLIANCE (AMOCS): The Manager, Chicago Aircraft Certification Office, FAA, ATTN: Wess Rouse, Small Airplane Project Manager, ACE-117C, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, Illinois 60018; telephone: (847) 294-8113; facsimile: (847) 294-7834; e-mail: wess.rouse@faa.gov; or Angie Kostopoulos, Composite Technical Specialist, ACE-116C, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, Illinois 60018; telephone: (847) 294-7426; facsimile: (847) 294-7834; e-mail: evangelia.kostopoulos@faa.gov, have the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.


AD; Raytheon Aircraft Company Model B300 Airplanes: Airworthiness Directives; Raytheon Aircraft Company Model B300 Airplanes, Federal Register, September 19, 2006, Volume 71, Number 181, Rules and Regulations, page 54762-54763, 14 CFR Part 39, Docket No. FAA-2005-22103; Directorate Identifier 2005-CE-42-AD; Amendment 39-14766; AD 2006-19-09, RIN 2120-AA64, Final rule.
[TEXT]  [PDF]
(This AD is effective on October 24, 2006. As of October 24, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation.)

PURPOSE: After Raytheon Aircraft Company made design changes to Model B300 Airplanes, the seats did not meet the ultimate load requirements of 14 CFR part 23 during structural testing. This AD is issued to prevent the passenger seats from failing during emergency landing conditions when there are high inertial loadings. Seat failure may injure passengers.

SUMMARY: This AD requires you to modify the cabin passenger seats by installing a modification kit on each passenger seat, removing the existing technical standard order (TSO) label, and re-identifying each modified passenger seat assembly with a new part number.

MODEL B300 AIRPLANES, SERIAL NUMBERS FL-1 THROUGH FL-289: This AD affects Model B300 airplanes, serial numbers FL-1 through FL-289, certificated in any category.

WITHIN 24 CALENDAR MONTHS OR 600 HOURS TIME-IN-SERVICE (TIS), WHICHEVER OCCURS FIRST: Unless already done, within 24 calendar months or 600 hours time-in-service after October 24, 2006, whichever occurs first, you must comply with the first part of this AD, which is to install a modification kit for each cabin passenger seat, as follows:
Install part number (P/N) 130-5108-0001 for left forward facing seats or right backward facing seats; and
Install P/N 130-5108-0002 for right forward facing seats or left backward facing seats.
Next, before further flight, after making the modification: Remove the TSO label on each cabin seat and re-identify each modified cabin seat assembly with the new P/N.

SERVICE BULLETINS: You must do the actions required by this AD following the instructions in Raytheon Aircraft Company Service Bulletin SB 25-3640, Rev. 1; Issued: May 2005, Revised: January 2006. To get a copy of this service information, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201; telephone: (800) 625-7043. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to:
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030.

ALTERNATIVE METHODS OF COMPLIANCE (AMOCS): The Manager, Wichita Aircraft Certification Office (ACO), FAA, ATTN: Steven E. Potter, Aerospace Engineer, Wichita ACO, Airframe and Services Branch, ACE-118W, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4124; facsimile: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.


AD; Stemme GmbH & Co. KG Model STEMME S10-VT Sailplanes: Airworthiness Directives; Stemme GmbH & Co. KG Model STEMME S10-VT Sailplanes, Federal Register, September 19, 2006, Volume 71, Number 181, Rules and Regulations, page 54757-54759, 14 CFR Part 39, Docket No. FAA-2006-25689; Directorate Identifier 2006-CE-45-AD; Amendment 39-14765; AD 2006-19-08, RIN 2120-AA64, Final rule; request for comments.
[TEXT]  [PDF]
(This AD is effective on October 10, 2006. As of October 10, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. Any public comments must be received by October 19, 2006.)

PURPOSE: Deformations and cracks at a bend in an exhaust pipe have been found in Stemme GmbH & Co. KG Model STEMME S10-VT Sailplanes. This AD is issued to detect and correct cracks in the exhaust pipes. Damaged exhaust pipes could cause exhaust gases to expand into the engine compartment and/or carbon monoxide (CO) to leak into the cockpit section.

SUMMARY: You must do a one-time inspection of all exhaust bends (each cylinder 1 to 4) in the area of the curvature bend near the cylinder flange, replace any damaged exhaust pipes found, and recondition the heat protection wrapping.

WITHIN THE NEXT 10 HOURS TIME-IN-SERVICE (TIS) AFTER OCTOBER 10, 2006: you must comply with the first part of this AD, which is to Inspect all exhaust bends (each cylinder 1 to 4) in the area of the curvature bend near the cylinder flange for deformations, cracks, and/ or flattening. Use a minimum 10X magnifier to aid the inspection. BEFORE FURTHER FLIGHT, after the inspection, if you find any damage (deformation, cracks, and/or flattening), replace the damaged exhaust pipe. AGAIN, BEFORE FURTHER FLIGHT, after the inspection and the replacement of any damaged pipes, recondition the heat protection wrapping.

PAY ATTENTION TO THE SUBJECT OF THIS AD WHEN DOING REGULAR INSPECTIONS, TOO: According to the Maintenance Manual an inspection of the condition of the exhaust pipes is scheduled for every 100 flight hours. It is recommended to pay special attention to this item when making this regular inspection.

SERVICE BULLETINS: You must do the actions required by this AD following the instructions in Stemme GmbH & Co. KG Service Bulletin A31-10-075 Am.-Index: 01.a, dated July 06, 2006. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact STEMME AG-Flugplatzstra[beta]e F2, Nr. 7, D-15344 Strausberg, Germany; telephone: +49.33.41/36 12-0; fax: +49.33 41/36 12-30. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/[fxsp0]federal--register/[fxsp0]code--of--federal--regulations/[fxsp0]ibr--locations.html or call (202) 741-6030.

ALTERNATIVE METHODS OF COMPLIANCE (AMOCS): The Manager, Standards Staff, FAA, ATTN: Gregory Davison, Glider Project Manager, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.


AD; Gippsland Aeronautics Pty. Ltd. Model GA8 Airplanes: Airworthiness Directives; Gippsland Aeronautics Pty. Ltd. Model GA8 Airplanes, Federal Register: September 20, 2006, Volume 71, Number 182, Rules and Regulations, page 54901-54902, 14 CFR Part 39, Docket No. FAA-2006-24955; Directorate Identifier 2006-CE-31-AD; Amendment 39-14768; AD 2006-19-11, RIN 2120-AA64, Final rule.
[TEXT]  [PDF]

(This AD IS effective October 25, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 25, 2006.)

PURPOSE: The ‘stops’ at the pilot and second occupant seat in certain Model GA8 airplanes are located in such a way that, at either seat's most forward position, aft movement of the control column can be restricted by the seat structure. If not corrected, this condition could lead to reduced controllability of the airplane in certain conditions.

SUMMARY: This AD is issued to require that the seat track rail of the pilot and second occupant seats is modified to add a new stop location in the specified airplanes.

MODEL GA8 AIRPLANES: This AD applies to Model GA8 airplanes, all serial numbers through GA8-05-088, certificated in any U.S. category.

AT THE NEXT REGULARLY SCHEDULED MAINTENANCE INSPECTION (E.G.
100 HOUR OR ANNUAL) THAT OCCURS 30 DAYS OR MORE AFTER OCTOBER 25,
2006, MODIFY THE PILOT AND SECOND OCCUPANT SEAT TRACK RAILS TO ADD A NEW STOP LOCATION, UNLESS IT HAS ALREADY BEEN DONE: Do the modification following Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2005-29, Issue 2, dated February 14, 2006.

RETURN TO AIRWORTHINESS: When complying with this AD, perform FAA-approved corrective actions before returning the product to an airworthy condition.

SERVICE BULLETIN:
The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.
For service information identified in this AD, contact Gippsland Aeronautics, PO Box 881, Morwell, Victoria 3840, Australia; telephone: + 61 (0) 3 5172 1200; facsimile: + 61 (0) 3 5172 1201; e-mail: support@gippsaero.com.
You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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/cfr/ibr-locations.html.

ALTERNATIVE METHODS OF COMPLIANCE (AMOCS): The Manager, Standards Staff, FAA, Attn: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.