Airworthiness Directives; Gulfstream Aerospace Corporation, 75908-75911 [2012-31036]

Download as PDF 75908 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Proposed Rules with a new bellcrank, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–27–55, dated June 15, 2011. ebenthall on DSK5TPTVN1PROD with (i) Actions for Certain Other Model DHC–8– 400 Series Airplanes For Model DHC–8–400, –401, and –402 airplanes that have accumulated more than 15,000 total flight hours as of the effective date of this AD: Within 600 flight hours after the effective date of this AD, measure the edge-to-edge length of the clevis holes of each bellcrank, and inspect for cracking of each bellcrank using liquid penetrant; in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–27–55, dated June 15, 2011. (1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than or equal to 0.218 inch: At the later of the compliance times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, rework or replace the bellcrank, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–27–55, dated June 15, 2011. (i) Within 6,000 flight hours after the effective date of this AD, but not to exceed 15,600 total flight hours. (ii) Within 1,200 flight hours after the effective date of this AD. (2) If no cracking is found, and any clevis hole edge-to-edge length is greater than 0.218 inch but less than or equal to 0.248 inch: Within 6,000 flight hours after the effective date of this AD, replace the bellcrank with a new bellcrank, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–27–55, dated June 15, 2011. (3) If no cracking is found, and any clevis hole edge-to-edge length is greater than 0.248 inch but less than or equal to 0.278 inch: Within 1,200 flight hours after the effective date of this AD, replace the bellcrank with a new bellcrank, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–27–55, dated June 15, 2011. (4) If any cracking is found, or any clevis hole edge-to-edge length exceeds 0.278 inch: Before further flight, replace the bellcrank with a new bellcrank, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–27–55, dated June 15, 2011. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7300; fax (516) 794–5531. Before using any approved AMOC, VerDate Mar<15>2010 06:27 Dec 22, 2012 Jkt 229001 notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (k) Related Information (1) Refer to MCAI Canadian Airworthiness Directive CF–2011–32, dated August 15, 2011, and the service bulletins specified in paragraphs (k)(1) (i) and (k)(1)(ii) of this AD, for related information. (i) Bombardier Service Bulletin 8–27–111, dated June 15, 2011. (ii) Bombardier Service Bulletin 84–27–55, dated June 15, 2011. (2) For service information identified in this AD, contact Bombardier, Inc., Q–Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 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. 2012–30925 Filed 12–21–12; 8:45 am] BILLING CODE 4910–13–P 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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 SUMMARY: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 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 pubs@gulfstream.com; 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. E:\FR\FM\26DEP1.SGM 26DEP1 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Proposed Rules 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: darby.mirocha@faa.gov. 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 75909 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 product Labor cost Inspection to determine if a certain part number is installed. Maintenance program revision 1 work-hour X $85 per hour = $85 ........................................ $0 $85 $30,345 1 work-hour X $85 per hour = $85 ........................................ $0 $85 $30,345 We estimate the following costs to do any necessary replacements that would Parts cost Cost on U.S. operators Action 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 ebenthall on DSK5TPTVN1PROD with Action Labor cost Parts cost Cost per product Replacement ................................................................. 24 work-hours X $85 per hour = $2,040 ...................... $7,600 $9,640 VerDate Mar<15>2010 06:27 Dec 22, 2012 Jkt 229001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\26DEP1.SGM 26DEP1 75910 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Proposed Rules 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. ebenthall on DSK5TPTVN1PROD with 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. VerDate Mar<15>2010 06:27 Dec 22, 2012 Jkt 229001 § 39.13 [Amended] 2. The FAA amends § 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. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 (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: darby.mirocha@faa.gov. (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, E:\FR\FM\26DEP1.SGM 26DEP1 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Proposed Rules GA 31402–2206; telephone 800–810–4853; fax 912–965–3520; email pubs@gulfstream.com; 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 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1230; Directorate Identifier 2011–NM–107–AD] RIN 2120–AA64 Airworthiness Directives; Embraer S.A. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) that applies to certain Embraer S.A. Model ERJ 170 and ERJ 190 airplanes. The existing AD currently requires, for certain airplanes, repetitively replacing the low-stage check valve and associated seals of the right hand (RH) engine’s engine bleed system with a new check valve and new seals, replacing the low pressure check valves (LPCV), and revising the maintenance program. For certain other airplanes, the existing AD requires replacing a certain low-stage check valve with an improved low-stage check valve. Since we issued that AD, we have received reports of uncommanded engine shutdowns on both Model ERJ 170 and ERJ 190 airplanes due to excessive wear and failure of LPCVs having certain part numbers. This proposed AD would also, for certain airplanes, require replacing certain LPCVs of the left-hand (LH) and RH engines, which would be an option for other airplanes. We are proposing this AD to prevent the possibility of a dual engine in-flight shutdown due to LPCV failure. DATES: We must receive comments on this proposed AD by February 11, 2013. ebenthall on DSK5TPTVN1PROD with SUMMARY: VerDate Mar<15>2010 06:27 Dec 22, 2012 Jkt 229001 You may send comments 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, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Embraer S.A., Technical Publications Section (PC 060), Av. Brigadeiro Faria Lima, 2170— ˜ Putim—12227–901 Sao Jose dos Campos—SP—BRASIL; telephone +55 12 3927–5852 or +55 12 3309–0732; fax +55 12 3927–7546; email distrib@embraer.com.br; Internet http:// www.flyembraer.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office 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 Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Cindy Ashforth, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–2768; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: 75911 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 based on 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 On June 23, 2010, we issued AD 2010–14–14, Amendment 39–16359 (75 FR 42585, July 22, 2010). That AD required actions intended to address an unsafe condition on Embraer S.A. Model ERJ 170 and ERJ 190 airplanes. Since we issued AD 2010–14–14, Amendment 39–16359 (75 FR 42585, July 22, 2010), there have been occurrences of uncommanded engine shutdowns on both Model ERJ 170 and Model ERJ 190 airplanes due to excessive wear and failure of LPCVs having part number 1001447–3 and 1001447–4. Both engines of the airplanes have the same valves, which leads to the possibility of a dual engine in-flight shutdown due to LPCV failure. ˆ The Agencia Nacional de Aviacao Civil ¸˜ (ANAC), which is the aviation authority for Brazil, has issued Brazilian Airworthiness Directives 2005–09–03R3 and 2006–11–01R6, both effective May 30, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI for Embraer S.A. Model ERJ 170 airplanes states: It has been found the occurrence of an engine in-flight shutdown * * * caused by the LPCV [low pressure check valves] failure P/N [part number] 1001447–3 with 3,900 Flight Hours (FH) installed on ERJ–170. This valve failed [to] open due [to] excessive wear. [I]t was found the occurrence of an engine shutdown on-ground, caused by the LPCV failure P/N 1001447–4 with 1,802 FH installed on ERJ–190 failed due [to] low cycle fatigue. Since the behavior of a valve P/N 1001447–4 removed from ERJ–190 is unknown on ERJ–170 and the P/N 1001447– 4 is common between ERJ–170 and ERJ–190 airplane fleet, an action is necessary to prevent the installation, in ERJ–170 airplanes, of LPCVs P/N 1001447–4 previously installed in ERJ–190 airplanes. Comments Invited * We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2012–1230; Directorate Identifier 2011–NM–107–AD’’ at the beginning of your comments. We specifically invite It has been found the occurrence of an engine in-flight shutdown * * * caused by the LPCV failure P/N [part number] 1001447– 3 with 3,900 Flight Hours (FH) installed on ERJ–170. This valve failed [to] open due [to] excessive wear. [I]t was found the occurrence of an engine shutdown on-ground, caused by PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 * * * * The MCAI for Embraer S.A. Model ERJ 190 airplanes states: E:\FR\FM\26DEP1.SGM 26DEP1

Agencies

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


-----------------------------------------------------------------------

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).

-----------------------------------------------------------------------

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 pubs@gulfstream.com; 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: 
darby.mirocha@faa.gov.

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
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------

    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.
----------------------------------------------------------------------------------------------------------------


[[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: darby.mirocha@faa.gov.
    (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 
pubs@gulfstream.com; 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