Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes

[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:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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:
    <bullet> 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.
    <bullet> 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.
    <bullet> 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.
    <bullet> 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.
    <bullet> 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.
    <bullet> 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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------

    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]
BILLING CODE 4910-13-P

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