[Federal Register: November 3, 2005 (Volume 70, Number 212)]
[Rules and Regulations]
[Page 66747-66749]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03no05-1]
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Rules and Regulations
Federal Register
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[[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 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:
[[Page 66748]]
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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.
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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: 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]
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