Airworthiness Directives; GROB-WERKE Model G120A Airplanes, 66747-66749 [05-21800]

Download as PDF 66747 Rules and Regulations Federal Register Vol. 70, No. 212 Thursday, November 3, 2005 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. 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 Airworthiness Directives; GROB– WERKE Model G120A Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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. VerDate Aug<31>2005 17:03 Nov 02, 2005 Jkt 208001 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 https:// 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: ADDRESSES: 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 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 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: E:\FR\FM\03NOR1.SGM 03NOR1 66748 Federal Register / Vol. 70, No. 212 / Thursday, November 3, 2005 / Rules and Regulations Labor cost Parts cost Total cost per airplane 1 work hour × $65 an hour = $65 ............................................................................... $20 $85 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: I § 39.13 Total cost on U.S. operators $85 × 6 = $510. [Amended] I 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: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. 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; (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 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 VerDate Aug<31>2005 17:03 Nov 02, 2005 Jkt 208001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\03NOR1.SGM 03NOR1 Federal Register / Vol. 70, No. 212 / Thursday, November 3, 2005 / Rules and Regulations 66749 Actions Compliance Procedures (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. (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 lefthand instrument panel.. 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. 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: https://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 https:// dms.dot.gov. The docket number is FAA– 2005–21998; Directorate Identifier 2005–CE– 40–AD. VerDate Aug<31>2005 17:03 Nov 02, 2005 Jkt 208001 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 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21835; Directorate Identifier 2005–CE–35–AD; Amendment 39– 14357; AD 2005–22–13] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Models PC–12 and PC–12/ 45 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Models PC–12 and PC–12/45 airplanes. This AD requires you to inspect the left and right main landing gear (MLG) assemblies for any part number (P/N) 532.10.12.077 or FAA-approved equivalent part number bolts that do not have white primed and painted heads; and replace any bolt found with new P/N 532.10.12.077F or FAA-approved equivalent part number bolts in all MLG assemblies. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct any P/N 532.10.12.077 or FAA-approved equivalent part number bolts that do not have white primed and painted heads, which could result in corrosion of the bolt and consequent failure of the bolt. This failure could lead to MLG collapse during airplane landing and take-off operations with consequent loss of airplane control. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 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 Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; email: SupportPC12@pilatus-aircraft.com or from Pilatus Business Aircraft Ltd., Product Support Department, 11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465–9099; facsimile: (303) 465–6040. 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– 0001 or on the Internet at https:// dms.dot.gov. The docket number is FAA–2005–21835; Directorate Identifier 2005–CE–35–AD. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; facsimile: (816) 329–4090. SUPPLEMENTARY INFORMATION: DATES: Discussion What events have caused this AD? The Federal Office for Civil Aviation (FOCA), which is the airworthiness authority for Switzerland, recently notified FAA that an unsafe condition may exist on certain Pilatus Models PC– 12 and PC–12/45 airplanes. The FOCA reports part number (P/N) 532.10.12.077 bolts that do not have white primed and painted heads are subject to corrosion. These bolts attach the hydraulic actuators to the left and right main landing gear (MLG) assemblies. The FOCA further reports the separation of a bolt head in an MLG assembly has occurred due to corrosion. The corrosion occurred because the bolt head was not primed and painted. E:\FR\FM\03NOR1.SGM 03NOR1

Agencies

[Federal Register Volume 70, Number 212 (Thursday, November 3, 2005)]
[Rules and Regulations]
[Pages 66747-66749]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-21800]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 70, No. 212 / Thursday, November 3, 2005 / 
Rules and Regulations

[[Page 66747]]



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


Airworthiness Directives; GROB-WERKE Model G120A Airplanes

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 https://
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:

[[Page 66748]]



----------------------------------------------------------------------------------------------------------------
                                                           Total cost per
              Labor cost                   Parts cost         airplane          Total cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $65 an hour = $65.......              $20               $85   $85 x 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

0
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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. FAA amends Sec.  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:              Within the next 50    Follow GROB Service
(i) Any signs of chafing       hours time-in-        Bulletin No.
 damage to the attachment      service (TIS) after   MSB1121-065, dated
 cables of switches below      December 19, 2005     July 1, 2005
 the switch panels of the      (the effective date
 left-hand instrument panel;   of this AD), unless
                               already done.
    (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

[[Page 66749]]

 
    (iii) If you find any     Before further        Follow GROB Service
     damaged (that is,         flight after the      Bulletin No.
     sharp) edge on the        inspection required   MSB1121-065, dated
     support tray for the      by paragraph (e)(1)   July 1, 2005.
     attachment cables of      of this AD.
     switches below the
     switch panels of the
     left-hand instrument
     panel, grind off any
     sharp edges and clean
     thoroughly.
(3) Apply anti-rub (padding   Before further        Follow GROB Service
 strips to the edge of the     flight after the      Bulletin No.
 support tray for the          inspection required   MSB1121-065, dated
 attachment cables of          by paragraph (e)(1)   July 1, 2005.
 switches below the switch     of this AD. This
 panels of the left-hand       modification is
 instrument panel..            required even if
                               damage is not found
                               during the
                               inspections.
------------------------------------------------------------------------

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: https://
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 https://
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

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