[Federal Register Volume 77, Number 247 (Wednesday, December 26, 2012)]
[Proposed Rules]
[Pages 75908-75911]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-31036]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1313; Directorate Identifier 2012-NM-080-AD]
RIN 2120-AA64


Airworthiness Directives; Gulfstream Aerospace Corporation

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Gulfstream Aerospace Corporation Model GV and GV-SP airplanes. This 
proposed AD was prompted by reports of two failures of the fuel boost 
pump and over-heat damage found on the internal components and external 
housing. This proposed AD would require doing an inspection to 
determine if fuel boost pumps having a certain part number are 
installed, replacing the fuel boost pumps having a certain part number, 
and revising the airplane maintenance program to include revised 
instructions for continued airworthiness. We are proposing this AD to 
prevent fuel leakage into the dry cavity of the boost pump and outside 
of the fuel pump, and to prevent capacitor clearance issues in the dry 
cavity, which together could result in an uncontrolled fire in the 
wheel well.

DATES: We must receive comments on this proposed AD by February 11, 
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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For Gulfstream, Triumph Aerostructures, and GE Aviation service 
information identified in this proposed 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 proposed 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.

[[Page 75909]]


FOR FURTHER INFORMATION CONTACT: Darby Mirocha, Aerospace Engineer, 
Propulsion and Services Branch, ACE-118A, FAA, Atlanta Aircraft 
Certification Office, 1701 Columbia Avenue, College Park, GA 30337; 
telephone (404) 474-5573; fax (404) 474-5606; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2012-1313; 
Directorate Identifier 2012-NM-080-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed 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 proposed AD.

Discussion

    We have received a report of failure of the fuel boost pump and 
over-heat damage found on the internal components and external housing. 
A subsequent investigation identified inadequate clearance between the 
internal capacitor and a printed circuit board as the root cause of the 
failure. Additionally, on other components, a damaged o-ring between 
the ``wet'' and ``dry'' cavities of the boost pump resulted in fuel 
ingress into the ``dry'' cavity. Product improvements have been 
incorporated into the boost pumps to modify the capacitor installation 
to prevent external shorting and incorporate an inspection port to 
allow for inspection of the ``dry'' cavity. This condition, if not 
corrected, could cause fuel leakage into the dry cavity of the boost 
pump and outside of the fuel pump, and capacitor clearance issues in 
the dry cavity, which together could result in an uncontrolled fire in 
the wheel well.

Relevant Service Information

    We reviewed Gulfstream V Service Bulletin 197 (for Model GV 
airplanes), and Gulfstream G550 Service Bulletin 122 (for Model GV-SP 
airplanes), both dated April 11, 2012, both including the following 
service information:
     Triumph Service Bulletin SB-TAGV/GVSP-28-JG0162, dated 
August 30, 2011.
     GE Service Bulletin 31760-28-100, dated February 15, 2011.

This service information describes procedures for doing an inspection 
to determine if fuel boost pumps having a certain part number are 
installed, and replacing the fuel boost pumps having a certain part 
number.

    We have also reviewed Gulfstream Document GV-GER-0003, Instructions 
for Continued Airworthiness, Fuel Boost Pump with Leak Check Port, 
dated November 24, 2010. This service information describes procedures 
for fuel leak checks of the fuel boost pump.

FAA's Determination

    We are proposing 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 these same type 
designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between the Proposed AD and the Service 
Information.''

Differences Between the Proposed AD and the Service Information

    Gulfstream V Service Bulletin 197 (for Model GV airplanes) and 
Gulfstream G550 Service Bulletin 122 (for Model GV-SP airplanes), both 
dated April 11, 2012, specify a compliance time of 42 months after the 
release of those service bulletins for accomplishing the actions in 
those service bulletins. This proposed AD requires a compliance time of 
36 months after the effective date of this proposed AD. In developing 
the compliance time, we considered not only the degree of urgency 
associated with addressing the subject unsafe condition, but the 
manufacturer's recommendation for an appropriate compliance time, the 
availability of required parts, and the practical aspect of doing the 
actions within an interval of time that corresponds to the typical 
scheduled maintenance for the majority of affected operators. This 
difference has been coordinated with Gulfstream.

Costs of Compliance

    We estimate that this proposed AD affects 357 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
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Inspection to determine if a         1 work-hour X $85 per hour               $0             $85         $30,345
 certain part number is installed.    = $85.
Maintenance program revision.......  1 work-hour X $85 per hour               $0             $85         $30,345
                                      = $85.
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    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement..................................  24 work-hours X $85 per hour =           $7,600           $9,640
                                                $2,040.
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[[Page 75910]]

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

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (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),
    (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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Gulfstream Aerospace Corporation: Docket No. FAA-2012-1313; 
Directorate Identifier 2012-NM-080-AD.

(a) Comments Due Date

    We must receive comments by February 11, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Gulfstream Aerospace Corporation Model GV 
and GV-SP airplanes, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 2822, Fuel boost pump.

(e) Unsafe Condition

    This AD was prompted reports of two failures of the fuel boost 
pump and over-heat damage found on the internal components and 
external housing. We are issuing this AD to prevent fuel leakage 
into the dry cavity of the boost pump and outside of the fuel pump, 
and to prevent capacitor clearance issues in the dry cavity, which 
together could result in an uncontrolled fire in the wheel well.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection to Determine the Part Number (P/N)

    Within 36 months after the effective date of this AD, inspect 
the fuel boost pumps to determine whether P/N 1159SCP500-5 is 
installed, in accordance with the Accomplishment Instructions of 
Gulfstream V Service Bulletin 197, dated April 11, 2012 (for Model 
GV airplanes); or Gulfstream G550 Service Bulletin 122, dated April 
11, 2012 (for Model GV-SP airplanes); including the service 
information specified in paragraphs (g)(1) and (g)(2) of this AD. A 
review of airplane maintenance records is acceptable in lieu of this 
inspection if the part number of the fuel boost pumps can be 
conclusively determined from that review.
    (1) Triumph Service Bulletin SB-TAGV/GVSP-28-JG0162, dated 
August 30, 2011.
    (2) GE Service Bulletin 31760-28-100, dated February 15, 2011.

(h) Replacement

    If the inspection required by paragraph (g) of this AD reveals a 
fuel boost pump with P/N 1159SCP500-5: Before further flight, 
replace the fuel boost pump with a serviceable pump having P/N 
1159SCP500-7, in accordance with Gulfstream V Service Bulletin 197, 
dated April 11, 2012 (for Model GV airplanes); or Gulfstream G550 
Service Bulletin 122, dated April 11, 2012 (for Model GV-SP 
airplanes); including the service information specified in 
paragraphs (h)(1) and (h)(2) of this AD.
    (1) Triumph Service Bulletin SB-TAGV/GVSP-28-JG0162, dated 
August 30, 2011.
    (2) GE Service Bulletin 31760-28-100, dated February 15, 2011.

(i) Maintenance Program Revision

    Within 500 flight hours after the effective date of this AD, 
revise the airplane maintenance program to include Gulfstream 
Document GV-GER-0003, Instructions for Continued Airworthiness, Fuel 
Boost Pump with Leak Check Port, dated November 24, 2010.
    (1) For airplanes on which fuel boost pump P/N 1159SCP500-5 has 
been replaced in accordance with paragraph (h) of this AD: The 
initial compliance time for the inspection is within 500 flight 
hours after doing the replacement specified in paragraph (h) of this 
AD.
    (2) For airplanes on which the inspection required by paragraph 
(g) of this AD reveals that a fuel boost pump with P/N 1159SCP500-7 
has been installed: After revising the airplane maintenance program, 
as required by paragraph (i) of this AD, the initial inspection is 
required before further flight after doing the inspection required 
by paragraph (g) of this AD.

(j) No Alternative Actions or Intervals

    After accomplishing the revision required by paragraph (i) of 
this AD, no alternative actions (e.g., inspections) or intervals may 
be used unless the actions or intervals are approved as an 
alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (l) of this AD.

(k) Parts Installation Prohibition

    As of the effective date of this AD, no person may install a 
fuel boost pump having P/N 1159SCP500-5 on any airplane.

(l) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta Aircraft Certification Office (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.

(m) Related Information

    (1) For more information about this AD, contact Darby Mirocha, 
Aerospace Engineer, Propulsion and Services Branch, ACE-118A, FAA, 
Atlanta ACO, 1701 Columbia Avenue, College Park, GA 30337; telephone 
(404) 474-5573; fax (404) 474-5606; email: [email protected].
    (2) For Gulfstream, Triumph Aerostructures, and GE Aviation 
service information identified in this AD, contact Gulfstream 
Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, 
Savannah,

[[Page 75911]]

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.

    Issued in Renton, Washington, on December 17, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-31036 Filed 12-21-12; 4:15 pm]
BILLING CODE 4910-13-P