Document headings vary by document type but may contain
                    the following: the agency or agencies that issued and signed a document
the number of the CFR title and the number of each part
                      the document amends, proposes to amend, or is directly
                      related to
the agency docket number / agency internal file number
the RIN which identifies each regulatory action listed in
                      the Unified Agenda of Federal Regulatory and Deregulatory
                      Actions See the
                    Document Drafting Handbook
                    for more details.
 Department of Transportation Federal Aviation Administration 14 CFR Part 39
[Docket No. FAA-2005-21998; Directorate Identifier 2005-CE-40-AD; Amendment 39-14358; AD 2005-22-14]
RIN 2120-AA64
 AGENCY: Federal Aviation Administration (FAA), DOT.
 ACTION: Final rule.
 SUMMARY: The FAA adopts a new airworthiness directive (AD) for all GROB-WERKE Model G120A airplanes. This AD requires you to inspect for signs of any chafing damage to the attachment cables of the switch panels below the left-hand instrument panel, any damaged switch below the switch panels of the left-hand instrument panel, any damaged (that is, sharp) edge of the support tray for the attachment cables of the switch panels below the left-hand instrument panel; correct any damage found during the inspection; and apply a layer of anti-rub (protective padding) strips to the edge of the support tray. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect, correct, and prevent chafing of the cables against the rear lip of the tray that holds the switch panels. Chafing of the electrical cables could result in smoke or fire in the cockpit.
 DATES: This AD becomes effective on December 19, 2005. As of December 19, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation.
 ADDRESSES: To get the service information identified in this AD, contact GROB Luft-und Raumfahrt, Lettenbachstrasse 9, D-86874 Tussenhausen-Mattsies, Federal Republic of Germany; telephone: 011 49 8268 998139; facsimile: 011 49 8268 998200. 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 20590-001 or on the Internet at 
                        *http://dms.dot.gov.*
                         The docket number is FAA-2005-21998; Directorate Identifier 2005-CE-40-AD.
 FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; facsimile: (816) 329-4090.


SUPPLEMENTARY INFORMATION: Discussion *What events have caused this AD?*
                     The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority for Germany, recently notified FAA that an unsafe condition may exist on all GROB Model G120A airplanes. The LBA reports that GROB received a report of smoke in the cockpit on a Model G120A airplane. The emergency avionic switch on the switch panel below the left-hand instrument panel was identified as the source of the smoke. Chafing of the cables against the rear lip of the tray that holds the switch panels caused damage of the cable insulation. This damage resulted in arcing and melting of insulation. *What is the potential impact if FAA took no action?*
                     Chafing of the electrical cables could result in smoke or fire in the cockpit. *Has FAA taken any action to this point?*
                     We issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all GROB-WERKE Model G120A airplanes. This proposal was published in the 
                    **Federal Register**
                     as a notice of proposed rulemaking (NPRM) on August 26, 2005 (70 FR 50223). The NPRM proposed to require you to inspect for signs of any chafing damage to the attachment cables of the switch panels below the left-hand instrument panel, any damaged switch below the switch panels of the left-hand instrument panel, any damaged (that is, sharp) edge of the support tray for the attachment cables of the switch panels below the left-hand instrument panel; correct any damage found during the inspection; and apply a layer of anti-rub (protective padding) strips to the edge of the support tray. Comments *Was the public invited to comment?*
                     We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal or on the determination of the cost to the public. Conclusion *What is FAA's final determination on this issue?*
                     We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: —Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and —Do not add any additional burden upon the public than was already proposed in the NPRM. Changes to 14 CFR Part 39—Effect on the AD *How does the revision to 14 CFR part 39 affect this AD?*
                     On July 10, 2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs the FAA's AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions. Costs of Compliance *How many airplanes does this AD impact?*
                     We estimate that this AD affects 6 airplanes in the U.S. registry. *What is the cost impact of this AD on owners/operators of the affected airplanes?*
                     We estimate the following costs to do this inspection, replacement of any damaged cable bundle, damaged switch, or grinding off any sharp edge on the support tray, and installation of the protective padding: 
                    ( print page 66748) Labor cost
Parts cost
Total cost per airplane
Total cost on U.S. 
                             operators1 work hour × $65 an hour = $65
$20
$85
$85 × 6 = $510.
 Authority for This Rulemaking *What authority does FAA have for issuing this rulemaking action?*
                     Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106 describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the agency's authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this AD. Regulatory Findings *Will this AD impact various entities?*
                     We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. *Will this AD involve a significant rule or regulatory action?*
                     For the reasons discussed above, I certify that this AD: 1. Is not a “significant regulatory action” under Executive Order 12866; 2. Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD (and other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under 
                    **ADDRESSES**
                    . Include “Docket No. FAA-2005-21998; Directorate Identifier 2005-CE-40-AD” in your request. List of Subjects in 14 CFR Part 39 Air transportation
Aircraft
Aviation safety
Incorporation by reference
Safety
 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39—AIRWORTHINESS DIRECTIVES
 1.The authority citation for part 39 continues to read as follows: Authority:
                        49 U.S.C. 106(g), 40113, 44701. § 39.13
 2.FAA amends § 39.13 by adding a new AD to read as follows: **2005-22-14 GROB-WERKE:**
                             Amendment 39-14358; Docket No. FAA-2005-21998; Directorate Identifier 2005-CE-40-AD. When Does This AD Become Effective? (a) This AD becomes effective on December 19, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Model G120A airplanes, all serial numbers, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified in this AD are intended to detect, correct, and prevent chafing of the cables against the rear lip of the tray that holds the switch panels. Chafing of the electrical cables could result in smoke or fire in the cockpit. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions
Compliance
Procedures(1) Inspect for: 
                                     (i) Any signs of chafing damage to the attachment cables of switches below the switch panels of the left-hand instrument panel;
Within the next 50 hours time-in-service (TIS) after December 19, 2005 (the effective date of this AD), unless already done
Follow GROB Service Bulletin No. MSB1121-065, dated July 1, 2005(ii) Any damaged switch on switch panels of the left-hand instrument panel; and(iii) Any damaged (that is, sharp) edge of the support tray for the attachment cables of switches below the switch panels of the left-hand instrument panel..(2) Correct any damage found as a result of the inspection required by paragraph (e)(1) of this AD:(i) If you find any signs of chafing damage to the attachment cables of switches below the switch panels of the left-hand instrument panel, replace the attachment cables;(ii) If you find any damaged switch below the switch panels of the left-hand instrument panel, replace the switch; and( print page 66749)(iii) If you find any damaged (that is, sharp) edge on the support tray for the attachment cables of switches below the switch panels of the left-hand instrument panel, grind off any sharp edges and clean thoroughly.
Before further flight after the inspection required by paragraph (e)(1) of this AD
Follow GROB Service Bulletin No. MSB1121-065, dated July 1, 2005.(3) Apply anti-rub (padding strips to the edge of the support tray for the attachment cables of switches below the switch panels of the left-hand instrument panel.
Before further flight after the inspection required by paragraph (e)(1) of this AD. This modification is required even if damage is not found during the inspections
Follow GROB Service Bulletin No. MSB1121-065, dated July 1, 2005.
 May I Request an Alternative Method of Compliance? (f) 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 Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; facsimile: (816) 329-4090. Is There Other Information That Relates to This Subject? (g) German AD Number D-2005-242, effective date: July 1, 2005, also addresses the subject of this AD. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in GROB Service Bulletin No. MSB1121-065, dated July 1, 2005. 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 GROB Luft-und Raumfahrt, Lettenbachstrasse 9, D-86874 Tussenhausen-Mattsies, Federal Republic of Germany; telephone: 011 49 8268 998139; facsimile: 011 49 8268 998200. 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. 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 20590-001 or on the Internet at 
                            *http://dms.dot.gov.*
                             The docket number is FAA-2005-21998; Directorate Identifier 2005-CE-40-AD. Issued in Kansas City, Missouri, on October 25, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.


[FR Doc. 05-21800 Filed 11-2-05; 8:45 am] BILLING CODE 4910-13-P