[Federal Register Volume 77, Number 242 (Monday, December 17, 2012)]
[Rules and Regulations]
[Pages 74579-74582]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-30058]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1225; Directorate Identifier 2012-NM-219-AD;
Amendment 39-17288; AD 2012-25-07]
RIN 2120-AA64
Airworthiness Directives; Gulfstream Aerospace Corporation
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Gulfstream Aerospace Corporation Model GIV-X airplanes. This AD
requires performing a modified system power-on self test (SPOST) of the
flap/stabilizer electronic control unit (FSECU), and revising the
airplane flight manual to incorporate these test procedures into the
daily preflight check. This AD was prompted by
[[Page 74580]]
reports indicating that the FSECU does not detect failures of the brake
feature within the horizontal stabilizer electric motor unit (HSEMU),
or failures of drive solenoids for hydraulic valves within the flap
hydraulic control module (FHCM) during the SPOST. We are issuing this
AD to detect and correct such failures, which could result in runaway
horizontal stabilizer pitch trim system and consequent loss of pitch
control.
DATES: This AD is effective December 17, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 17,
2012.
We must receive comments on this AD by January 31, 2013.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Gulfstream
Aerospace Corporation, Technical Publications Dept., P.O. Box 2206,
Savannah, GA 31402-2206; telephone 800-810-4853; fax 912-965-3520;
email [email protected]; Internet http://www.gulfstream.com/product_support/technical_pubs/pubs/index.htm. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanford Proveaux, Aerospace Engineer,
Continued Operational Safety and Certificate Management Branch, ACE-
102A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia
Avenue, College Park, Georgia 30337; phone: 404-474-5566; fax: 404-474-
5606; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We have received reports that the flap/stabilizer electronic
control unit (FSECU) is not detecting failures of the brake feature in
the horizontal stabilizer electric motor unit (HSEMU), or failures of
drive solenoids for hydraulic valves in the flap hydraulic control
module (FHCM) during the system power-on self test (SPOST). The
potential for undetected horizontal stabilizer actuator (HSA) brake
failures results from the FSECU executing its SPOST before 115VAC and
hydraulic power are available during the airplane power-on sequence.
The root cause of this issue is the failure of the system power-up test
logic to first consider whether hydraulic and electrical power have
been supplied to the system articles under test; the test logic
therefore does not provide accurate information about the condition of
the articles. Failure to test the brake-holding torque functionality
and capability exposes the airplane to a potential latent failure of a
protective feature critical to the safe operation of the horizontal
stabilizer system. These conditions, if not corrected, could result in
a potential runaway horizontal stabilizer pitch trim system and
consequent loss of pitch control. Further, failure of the FHCM drive
solenoid valves to halt uncommanded flap motion could result in
uncommanded flap motion or flap runaway.
Relevant Service Information
We reviewed the following service information:
Gulfstream G350 Alert Customer Bulletin 11, including
Service Reply Card, dated December 4, 2012, which includes Revision 31,
dated December 4, 2012, of the Gulfstream G350 Airplane Flight Manual
Document GAC-AC-G350-OPS-0001.
Gulfstream G450 Alert Customer Bulletin 11, including
Service Reply Card, dated December 4, 2012, which includes Revision 33,
dated December 4, 2012, of the Gulfstream G450 Airplane Flight Manual
Document GAC-AC-G450-OPS-0001.
Section 1-27-40, ``Flap/Stabilizer System Preflight
Check,'' of the Gulfstream G350 Airplane Flight Manual Document GAC-AC-
G350-OPS-0001, Revision 31, dated December 4, 2012.
Section 1-27-40, ``Flap/Stabilizer System Preflight
Check,'' of the Gulfstream G450 Airplane Flight Manual Document GAC-AC-
G450-OPS-0001, Revision 33, dated December 4, 2012.
Section 2-03-20, ``Before Starting Engines,'' of the
Gulfstream G350 Airplane Flight Manual Document GAC-AC-G350-OPS-0001,
Revision 31, dated December 4, 2012.
Section 2-03-20, ``Before Starting Engines,'' of the
Gulfstream G450 Airplane Flight Manual Document GAC-AC-G450-OPS-0001,
Revision 33, dated December 4, 2012.
For information on the procedures and compliance times, see this
service information at http://www.regulations.gov by searching for
Docket No. FAA-2012-1225.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
This AD requires accomplishing the actions specified in the service
information identified previously, except as discussed under
``Differences Between the AD and the Service Information.''
Differences Between the AD and the Service Information
This AD requires compliance within 3 days. However, these actions
are recommended before further flight by Gulfstream G350 Alert Customer
Bulletin 11, dated December 4, 2012; and Gulfstream G450 Alert Customer
Bulletin 11, dated December 4, 2012. We have determined that the 3-day
compliance time required by this AD will adequately ensure safety while
avoiding the need to ground the fleet.
Although the service information recommends that operators contact
Gulfstream if a successful test is not achieved, this AD requires
operators to repair those conditions before further flight in
accordance with a method approved by the FAA.
[[Page 74581]]
Interim Action
We consider this AD interim action. Gulfstream is in the process of
updating software intended to terminate the actions required by this
AD. Once this upgrade is developed, approved, and available, we might
consider further rulemaking to require the upgraded software.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
failure of the brake feature in the HSEMU could result in a runaway
horizontal stabilizer pitch trim system which, if left uncorrected,
could result in loss of airplane pitch control. Therefore, we find that
notice and opportunity for prior public comment are impracticable and
that good cause exists for making this amendment effective in less than
30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include the docket number FAA-2012-1225 and
Directorate Identifier 2012-NM-219-AD at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. We will
consider all comments received by the closing date and may amend this
AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 200 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Preflight procedure test.............. 1 work-hour x $85 per $0 $85 $17,000
hour = $85.
AFM revision.......................... 1 work-hour x $85 per 0 85 17,000
hour = $85.
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
Authority for This Rulemaking
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
rulemaking action.
Regulatory Findings
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.
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 DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
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 FAA amends 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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2012-25-07 Gulfstream Aerospace Corporation: Amendment 39-17288;
Docket No. FAA-2012-1225; Directorate Identifier 2012-NM-219-AD.
(a) Effective Date
This AD is effective December 17, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Gulfstream Aerospace Corporation Model GIV-X
airplanes, certificated in any category, serial numbers 4001 through
4271 inclusive.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 27, Flight controls.
(e) Unsafe Condition
This AD was prompted by reports indicating that the flap/
stabilizer electronic control unit (FSECU) does not detect failures
of the brake feature within the horizontal stabilizer electric motor
unit (HSEMU), or failures of the drive solenoids for hydraulic
valves within the flap hydraulic control module (FHCM) during the
system power-on self test (SPOST). We are issuing this AD to detect
and correct such failures, which could result in runaway horizontal
stabilizer pitch trim system and consequent loss of pitch control.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 74582]]
(g) SPOST
Within 3 days after the effective date of this AD, perform an
SPOST of the FSECU, in accordance with the applicable service
information identified in paragraph (h)(1) or (h)(2) of this AD.
(1) For Model GIV-X (G350) airplanes: Use Gulfstream G350 Alert
Customer Bulletin 11, dated December 4, 2012, excluding Service
Reply Card, dated December 4, 2012, and excluding Revision 31, dated
December 4, 2012, of the Gulfstream G350 Airplane Flight Manual
Document GAC-AC-G350-OPS-0001.
(2) For Model GIV-X (G450) airplanes: Use Gulfstream G450 Alert
Customer Bulletin 11, dated December 4, 2012, excluding Service
Reply Card, dated December 4, 2012, and excluding Revision 33, dated
December 4, 2012, of the Gulfstream G450 Airplane Flight Manual
Document GAC-AC-G450-OPS-0001.
(h) Revision of Aircraft Flight Manual (AFM)
Before further flight after the FSECU passes the SPOST required
by paragraph (g) of this AD, revise the Normal Procedures and
Limitations sections of the AFM to incorporate the information
identified in paragraph (g)(1) or (g)(2) of this AD, as applicable.
(1) For Model GIV-X (G350) airplanes: Incorporate the
information in Section 1-27-40, ``Flap/Stabilizer System Preflight
Check,'' and Section 2-03-20, ``Before Starting Engines,'' of the
Gulfstream G350 Airplane Flight Manual Document GAC-AC-G350-OPS-
0001, Revision 31, dated December 4, 2012. This may be accomplished
by inserting into the AFM a copy of Gulfstream G350 Airplane Flight
Manual Document GAC-AC-G350-OPS-0001, Revision 31, dated December 4,
2012.
(2) For Model GIV-X (G450) airplanes: Section 1-27-40, ``Flap/
Stabilizer System Preflight Check,'' and Section 2-03-20, ``Before
Starting Engines,'' of the Gulfstream G450 Airplane Flight Manual
Document GAC-AC-G450-OPS-0001, Revision 33, dated December 4, 2012.
This may be accomplished by inserting into the AFM a copy of
Gulfstream G450 Airplane Flight Manual Document GAC-AC-G450-OPS-
0001, Revision 33, dated December 4, 2012.
(i) Corrective Action for Failed SPOST
If the FSECU fails any SPOST required by this AD or as specified
in the applicable AFM, repair before further flight in accordance
with a method approved by the Manager, Atlanta Aircraft
Certification Office (ACO), FAA. For a repair method to be approved
by the Manager, Atlanta ACO, as required by this paragraph, the
Manager's approval letter must specifically refer to this AD.
(j) Special Flight Permit
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Atlanta ACO, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
ACO, send it to the attention of the person identified in the
Related Information section of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(l) Related Information
For more information about this AD, contact Sanford Proveaux,
Aerospace Engineer, Continued Operational Safety and Certificate
Management Branch, ACE-102A, FAA, Atlanta Aircraft Certification
Office (ACO), 1701 Columbia Avenue, College Park, Georgia 30337;
phone: 404-474-5566; fax: 404-474-5606; email:
[email protected].
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Gulfstream G350 Alert Customer Bulletin 11, dated December
4, 2012.
(ii) Gulfstream G450 Alert Customer Bulletin 11, dated December
4, 2012.
(iii) Section 1-27-40, ``Flap/Stabilizer System Preflight
Check,'' of the Gulfstream G350 Airplane Flight Manual Document GAC-
AC-G350-OPS-0001, Revision 31, dated December 4, 2012. The document
number of this document is identified on the revision transmittal
page and the first page of the Record of Revisions; no other page of
this document contains this information.
(iv) Section 1-27-40, ``Flap/Stabilizer System Preflight
Check,'' of the Gulfstream G450 Airplane Flight Manual Document GAC-
AC-G450-OPS-0001, Revision 33, dated December 4, 2012. The document
number of this document is identified on the revision transmittal
page and the first page of the Record of Revisions; no other page of
this document contains this information.
(v) Section 2-03-20, ``Before Starting Engines,'' of the
Gulfstream G350 Airplane Flight Manual Document GAC-AC-G350-OPS-
0001, Revision 31, dated December 4, 2012. The document number of
this document is identified on the revision transmittal page and the
first page of the Record of Revisions; no other page of this
document contains this information.
(vi) Section 2-03-20, ``Before Starting Engines,'' of the
Gulfstream G450 Airplane Flight Manual Document GAC-AC-G450-OPS-
0001, Revision 33, dated December 4, 2012. The document number of
this document is identified on the revision transmittal page and the
first page of the Record of Revisions; no other page of this
document contains this information.
(3) For service information identified in this AD, contact
Gulfstream Aerospace Corporation, Technical Publications Dept., P.O.
Box 2206, Savannah, GA 31402-2206; telephone 800-810-4853; fax 912-
965-3520; email [email protected]; Internet http://www.gulfstream.com/product_support/technical_pubs/pubs/index.htm.
(4) You may view this service information at FAA, Transport
Airplane Directorate, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability
of this material at the FAA, call 425-227-1221.
(5) You may view this service information that is incorporated
by reference 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.
Issued in Renton, Washington, on December 7, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-30058 Filed 12-14-12; 8:45 am]
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