Airworthiness Directives; Boeing Model 767 Airplanes, 21166-21169 [E7-8175]

Download as PDF 21166 Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules TABLE 1.—EXCEPTIONS TO APPLICABILITY Airplane model Configuration Airbus modifications installed in production A330, A340–200, –300 ...................................... A330, A340–200, –300 ...................................... A340–500 ........................................................... With Modification 40161 (optional Type A door 3). Without Modification 40161 (Type 1 door 3) ... ........................................................................... A340–600 ........................................................... ........................................................................... 50806, 50807, 55071, and 55072. 50806 and 55071. Either 50806, 50807, and 55071, or 50806 and 55071. 50806, 50808, 55071, and 55073. TABLE 2.—EXCEPTIONS TO APPLICABILITY Airplane model Airbus Service Bulletins installed in service A330 ............................................ A340–200, –300 .......................... A340–500, –600 .......................... A330–25–3173, Revision 01, dated August 2, 2006; and A330–25–3301, dated March 24, 2006. A340–25–4191, Revision 01, dated August 2, 2006; and A340–25–4273, dated March 24, 2006. A340–25–5004, Revision 01, dated August 2, 2006; and A340–25–5110, dated March 24, 2006. jlentini on PROD1PC65 with PROPOSAL Reason (d) The mandatory continuing airworthiness information (MCAI) states that several operators have reported nonautomatic deployment of slide rafts during ground operational testing. In all cases, the slide raft released correctly from the door but did not inflate automatically. Pulling the manual backup handle correctly inflated the slide raft. Investigation conducted by the slide raft manufacturer showed that nonautomatic deployments have two potential root causes: Non-opening of the lacing; and stiffness and stiction (static friction) on the painted inflatable material. This situation, if not corrected, could delay the evacuation of passengers in case of an emergency. A new design solution has been developed to ensure the automatic slide raft deployment, which consists of: continuous ‘‘speed lacing’’ cord and new soft covers with rounded grommets (this modification ensures that the lacing opens); and a new shorter firing cable, a new anchor block for the slide raft packboard and a new folding procedure (this modification ensures automatic deployment regardless of the inflatable paint condition). Both modifications together ensure the automatic deployment function. The MCAI requires accomplishment of the set of modifications. Actions and Compliance (e) Unless already done, do the following actions. (1) For slide raft P/Ns 7A1508–003/–005/ –007/–023/–025/–027/–029/–115; P/Ns 7A1539–003/–004/–005/–006/–007/–008/ –023/–024/–025/–026/–027/–028/–029/–030/ –115/ –116; P/Ns 7A1510–003/–004/–005/– 006/–007/–008/–023/–024/–025/–026/–027/ –028/–029/ –030/–115/–116; and P/Ns 4A3934–1/–2/–001/–002: No later than 36 months after the effective date of this AD, modify the slide raft in accordance with the instructions given in Airbus Service Bulletin A330–25–3173, A340–25–4191, or A340–25– 5004, all Revision 01, all dated August 2, 2006; as applicable; and modify the slide raft assembly of each door in accordance with the instructions given in Airbus Service Bulletin A330–25–3301, A340–25–4273, or A340–25– 5110, all dated March 24, 2006; as applicable. (2) For slide raft P/Ns 7A1508–033/–035/ –037/–119/–121; P/Ns 7A1539–033/–034/ VerDate Aug<31>2005 16:35 Apr 27, 2007 Jkt 211001 –035/–036/–037/ –038/–119/–120/–121/–122; P/Ns 7A1510– 033/–034/–035/–036/–037/–038/ –119/–120/ –121/–122; and P/Ns 4A3934–5/–6/–7/–8: No later than 36 months after the effective date of this AD, modify the slide raft assembly of each door in accordance with the instructions given in Airbus Service Bulletin A330–25–3301, A340–25–4273, or A340–25– 5110, all dated March 24, 2006; as applicable. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (f) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, ATTN: Tim Backman, Aerospace Engineer, 1601 Lind Avenue, SW., Renton, Washington 98057–3356, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (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. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (g) Refer to MCAI EASA Airworthiness Directive 2006–0354, dated November 28, 2006; and the Airbus Service Bulletins PO 00000 Frm 00042 Fmt 4702 Sfmt 4702 specified in Table 3 of this AD for related information. TABLE 3.—AIRBUS SERVICE BULLETINS Service Bulletin A330–25–3173 A340–25–4191 A340–25–5004 A330–25–3301 A340–25–4273 A340–25–5110 Revision level Date 01 ........ 01 ........ 01 ........ Original Original Original August 2, 2006. August 2, 2006. August 2, 2006. March 24, 2006. March 24, 2006. March 24, 2006. Issued in Renton, Washington, on April 23, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–8172 Filed 4–27–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28035; Directorate Identifier 2006–NM–293–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 767 airplanes. This proposed AD would require sealing certain fasteners and stiffeners in the fuel tank, and changing certain wire bundle clamp configurations on the fuel E:\FR\FM\30APP1.SGM 30APP1 Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules tank walls. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to prevent possible ignition sources in the auxiliary fuel tank, main fuel tanks, and surge tanks caused by a wiring short or lightning strike, which could result in fuel tank explosions and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by June 14, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Judy Coyle, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6497; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: jlentini on PROD1PC65 with PROPOSAL Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2007–28035; Directorate Identifier 2006–NM–293–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA VerDate Aug<31>2005 16:35 Apr 27, 2007 Jkt 211001 personnel concerning this proposed AD. Using the search function of that web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address PO 00000 Frm 00043 Fmt 4702 Sfmt 4702 21167 unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. A safety assessment by Boeing identified a certain fastener type in the fuel tank walls that has an insufficient bond to the structure. These fasteners can be a path for electrical energy to enter the fuel tank if a wiring short occurs in a wire bundle installed along the fuel tank boundary structure, or if lightning strikes a wing surface. If energy from a wiring short or lightning strike goes through these fasteners, arcing can occur at the ends of the fasteners in the fuel tank. The ends of the fasteners in the fuel tank do not have sufficient electrical insulation to contain the energy from the arcs. This condition, if not corrected, could result in a potential ignition source inside a fuel tank. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 767–57A0100, dated August 21, 2006. The service bulletin describes procedures for sealing the ends of the fasteners on the brackets that hold the vortex generators, and, for certain airplanes, sealing the ends of fasteners on certain stiffeners on the rear spar. We have also reviewed Boeing Alert Service Bulletin 767–57A0102, dated October 25, 2006. The service bulletin describes procedures for changing the wire bundle clamp configurations at specified locations on the fuel tank walls, and sealing the fasteners and certain stiffeners at specified locations in the fuel tank. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. E:\FR\FM\30APP1.SGM 30APP1 21168 Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously. Costs of Compliance There are about 925 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. There are no U.S.-registered airplanes in Group 3 of Service Bulletin 767– 57A0102. The average labor rate is $80 per work hour. ESTIMATED COSTS Service bulletin Group Work hours Cost per airplane Parts Number of U.S.registered airplanes Fleet cost 767–57A0100 ................................................................... 1 2 6 114 (1) (1) $480 9,120 341 21 $163,680 191,520 767–57A0102 ................................................................... 1 2 3 246 874 24 $1,632 1,304 338 21,312 71,224 2,258 341 21 0 7,267,392 1,495,704 0 (1) Minimal. jlentini on PROD1PC65 with PROPOSAL 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 have 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 that the 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); and 3. Will not have a significant economic impact, positive or negative, VerDate Aug<31>2005 16:35 Apr 27, 2007 Jkt 211001 on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2007–28035; Directorate Identifier 2006–NM–293–AD. Comments Due Date (a) The FAA must receive comments on this AD action by June 14, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Model 767–200, –300, –300F, and –400ER series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 767–57A0100, dated August 21, 2006; and Boeing Alert PO 00000 Frm 00044 Fmt 4702 Sfmt 4702 Service Bulletin 767–57A0102, dated October 25, 2006. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent possible ignition sources in the auxiliary fuel tank, main fuel tanks, and surge tanks caused by a wiring short or lightning strike, which could result in fuel tank explosions and consequent loss of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Fastener Sealant Application (f) For airplanes identified in Boeing Alert Service Bulletin 767–57A0100, dated August 21, 2006: Within 60 months after the effective date of this AD, seal the ends of the fasteners on the brackets that hold the vortex generators, and seal the ends of the fasteners on certain stiffeners on the rear spar, as applicable. Do the actions in accordance with the Accomplishment Instructions of the service bulletin. Wire Bundle Sleeve and Clamp Installation and Fastener Sealant Application (g) For airplanes identified in Boeing Alert Service Bulletin 767–57A0102, dated October 25, 2006: Within 60 months after the effective date of this AD, change the wire bundle clamp configurations at specified locations on the fuel tank walls, and seal the fasteners and certain stiffeners at specified locations on the fuel tank. Do the actions in accordance with the Accomplishment Instructions of the service bulletin. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. E:\FR\FM\30APP1.SGM 30APP1 Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Issued in Renton, Washington, on April 17, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–8175 Filed 4–27–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24978; Directorate Identifier 2006–NM–108–AD] RIN 2120–AA64 • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1 L5A (D800–0024), for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: William Bond, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5253; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Comments Invited Airworthiness Directives; McDonnell Douglas Model 717–200 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. jlentini on PROD1PC65 with PROPOSAL AGENCY: SUMMARY: The FAA is revising an earlier proposed airworthiness directive (AD) for certain McDonnell Douglas Model 717–200 airplanes. The original NPRM would have required modifying the fuel boost pump container of the center tank. The original NPRM resulted from fuel system reviews conducted by the manufacturer. This action revises the original NPRM by adding airplanes to the applicability. We are proposing this supplemental NPRM to prevent exposing the fuel pump container vapor area to electrical arcing during a fuel pump motor case or connector burn through, which could result in a fuel tank explosion. DATES: We must receive comments on this supplemental NPRM by May 25, 2007. ADDRESSES: Use one of the following addresses to submit comments on this supplemental NPRM. • DOT Docket web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. VerDate Aug<31>2005 16:35 Apr 27, 2007 Jkt 211001 We invite you to submit any relevant written data, views, or arguments regarding this supplemental NPRM. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA 2006–24978; Directorate Identifier 2006–NM–108–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this supplemental NPRM. We will consider all comments received by the closing date and may amend this supplemental NPRM in light of those comments. We will post all comments submitted, without change, to https://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this supplemental NPRM. Using the search function of that web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https://dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza PO 00000 Frm 00045 Fmt 4702 Sfmt 4702 21169 level in the Nassif Building at the DOT street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We proposed to amend 14 CFR part 39 with a notice of proposed rulemaking (NPRM) for an AD (the ‘‘original NPRM’’) for certain McDonnell Douglas Model 717–200 airplanes. The original NPRM was published in the Federal Register on June 8, 2006 (71 FR 33262). The original NPRM proposed to require modifying the fuel boost pump container of the center tank. Comments We have considered the following comments on the original NPRM. Support for the NPRM AirTran Airways supports the proposed actions specified in the NPRM. Request To Refer to Latest Revision of Service Bulletin AirTran Airways and Boeing request that we reference Boeing Service Bulletin 717–28–0013, Revision 1, dated April 7, 2006, in the NPRM (we referred to Boeing Service Bulletin 717–28–0013, dated July 28, 2004, as the appropriate source of service information for doing the actions specified in the NPRM). AirTran Airways also requests that we give credit for actions done in accordance with the original issue. Boeing commented that there was additional work required by Revision 1, but in a subsequent comment Boeing states that this was in error and that no additional work was needed. Boeing also notes that Revision 2 of the service bulletin is being drafted. We agree to revise this AD to refer to the latest revision of the service bulletin as the appropriate source of service information. We have reviewed Boeing Service Bulletin 717–28–0013, Revision 1, dated April 7, 2006; and Boeing Service Bulletin 717–28–0013, Revision 2, dated September 13, 2006. The service bulletins contain essentially the same actions as described in the original issue of the service bulletin. However, Revision 1 of the service bulletin adds new airplanes to the effectivity (fuselages number 5136 through 5146), clarifies the configuration table, and clarifies the installation of the hat and cover assembles. Revision 2 of the service bulletin revises the parts pricing and clarifies the notes in the figures. We have revised this AD to refer to Revision 2 of the service bulletin. E:\FR\FM\30APP1.SGM 30APP1

Agencies

[Federal Register Volume 72, Number 82 (Monday, April 30, 2007)]
[Proposed Rules]
[Pages 21166-21169]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-8175]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28035; Directorate Identifier 2006-NM-293-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing Model 767 airplanes. This proposed AD would require 
sealing certain fasteners and stiffeners in the fuel tank, and changing 
certain wire bundle clamp configurations on the fuel

[[Page 21167]]

tank walls. This proposed AD results from fuel system reviews conducted 
by the manufacturer. We are proposing this AD to prevent possible 
ignition sources in the auxiliary fuel tank, main fuel tanks, and surge 
tanks caused by a wiring short or lightning strike, which could result 
in fuel tank explosions and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by June 14, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for the service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Judy Coyle, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 917-6497; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2007-
28035; Directorate Identifier 2006-NM-293-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation No. 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: single failures, single failures in 
combination with a latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    We have determined that the actions identified in this AD are 
necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.
    A safety assessment by Boeing identified a certain fastener type in 
the fuel tank walls that has an insufficient bond to the structure. 
These fasteners can be a path for electrical energy to enter the fuel 
tank if a wiring short occurs in a wire bundle installed along the fuel 
tank boundary structure, or if lightning strikes a wing surface. If 
energy from a wiring short or lightning strike goes through these 
fasteners, arcing can occur at the ends of the fasteners in the fuel 
tank. The ends of the fasteners in the fuel tank do not have sufficient 
electrical insulation to contain the energy from the arcs. This 
condition, if not corrected, could result in a potential ignition 
source inside a fuel tank.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 767-57A0100, dated 
August 21, 2006. The service bulletin describes procedures for sealing 
the ends of the fasteners on the brackets that hold the vortex 
generators, and, for certain airplanes, sealing the ends of fasteners 
on certain stiffeners on the rear spar.
    We have also reviewed Boeing Alert Service Bulletin 767-57A0102, 
dated October 25, 2006. The service bulletin describes procedures for 
changing the wire bundle clamp configurations at specified locations on 
the fuel tank walls, and sealing the fasteners and certain stiffeners 
at specified locations in the fuel tank.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

[[Page 21168]]

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously.

Costs of Compliance

    There are about 925 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD. There are no U.S.-
registered airplanes in Group 3 of Service Bulletin 767-57A0102. The 
average labor rate is $80 per work hour.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Number of
                                                                             Cost per      U.S.-
         Service bulletin              Group      Work hours     Parts       airplane    registered   Fleet cost
                                                                                         airplanes
----------------------------------------------------------------------------------------------------------------
767-57A0100.......................            1            6        (\1\)         $480          341     $163,680
                                              2          114        (\1\)        9,120           21      191,520
----------------------------------------------------------------------------------------------------------------
767-57A0102.......................            1          246       $1,632       21,312          341    7,267,392
                                              2          874        1,304       71,224           21    1,495,704
                                              3           24          338        2,258            0            0
----------------------------------------------------------------------------------------------------------------
(1) Minimal.

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 have 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 that the 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); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2007-28035; Directorate Identifier 2006-NM-
293-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by June 14, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model 767-200, -300, -300F, and -400ER 
series airplanes; certificated in any category; as identified in 
Boeing Alert Service Bulletin 767-57A0100, dated August 21, 2006; 
and Boeing Alert Service Bulletin 767-57A0102, dated October 25, 
2006.

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent possible ignition 
sources in the auxiliary fuel tank, main fuel tanks, and surge tanks 
caused by a wiring short or lightning strike, which could result in 
fuel tank explosions and consequent loss of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Fastener Sealant Application

    (f) For airplanes identified in Boeing Alert Service Bulletin 
767-57A0100, dated August 21, 2006: Within 60 months after the 
effective date of this AD, seal the ends of the fasteners on the 
brackets that hold the vortex generators, and seal the ends of the 
fasteners on certain stiffeners on the rear spar, as applicable. Do 
the actions in accordance with the Accomplishment Instructions of 
the service bulletin.

Wire Bundle Sleeve and Clamp Installation and Fastener Sealant 
Application

    (g) For airplanes identified in Boeing Alert Service Bulletin 
767-57A0102, dated October 25, 2006: Within 60 months after the 
effective date of this AD, change the wire bundle clamp 
configurations at specified locations on the fuel tank walls, and 
seal the fasteners and certain stiffeners at specified locations on 
the fuel tank. Do the actions in accordance with the Accomplishment 
Instructions of the service bulletin.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.

[[Page 21169]]

    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

    Issued in Renton, Washington, on April 17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-8175 Filed 4-27-07; 8:45 am]
BILLING CODE 4910-13-P
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