Airworthiness Directives; Boeing Model 767-200, -300, and -300F Series Airplanes, 33926-33928 [E7-11926]

Download as PDF 33926 Federal Register / Vol. 72, No. 118 / Wednesday, June 20, 2007 / Proposed Rules airworthiness approvals for imports and exports. The comment period closed on June 11, 2007. By requests dated May 3, May 31, and June 6, Hartzell Propeller, Inc. (Hartzell), McCauley Propeller Systems (McCauley), and the General Aviation Manufacturers Association (GAMA), respectively, asked that the comment period be extended by 60 days to permit a more careful review and consideration of the proposed rule. The FAA has determined that reopening the comment period for 45 days will allow Hartzell, McCauley, GAMA, and others sufficient time for a more thorough review of applicable issues and questions raised by the NPRM, and for the drafting of responsive comments. In order, therefore, to give all interested persons additional time to complete their comments, the FAA finds that it is in the public interest to reopen the comment period for fortyfive (45) days. Issued in Washington, DC, on June 14, 2007. Dorenda D. Baker, Deputy Director, Aircraft Certification Service. [FR Doc. 07–3050 Filed 6–15–07; 4:02 pm] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2003–NM–67–AD] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135 and EMB–145 Series Airplanes Actions That Occurred Since the NPRM Was Issued Federal Aviation Administration, DOT. ACTION: Proposed rule; withdrawal. AGENCY: This action withdraws a notice of proposed rulemaking (NPRM) that proposed a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB–135 and EMB– 145 series airplanes. That action would have required an inspection of the base and support surfaces of the glide slope antenna and of certain electrical connectors of the navigation system, and applicable corrective actions if necessary. Since the issuance of the NPRM, we have received new data showing that the proposed inspection and corrective actions will not eliminate the display of erroneous or misleading rwilkins on PROD1PC63 with PROPOSALS SUMMARY: VerDate Aug<31>2005 17:23 Jun 19, 2007 Jkt 211001 information to the flightcrew in the cockpit. However, we have been informed that the navigation system manufacturer has developed effective corrective actions to address the unsafe condition identified in the NPRM. Since we issued the NPRM, we have issued other rulemaking, which provides corrective actions for the identified unsafe condition. Accordingly, the proposed rule is withdrawn. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to add a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB–135 and EMB–145 series airplanes, was published in the Federal Register as a Notice of Proposed Rulemaking (NPRM) on March 11, 2004 (69 FR 11549). The proposed rule would have required an inspection of the base and support surfaces of the glide slope antenna and of certain electrical connectors of the navigation system, and applicable corrective actions if necessary. That action resulted from reports of degradation in the performance of the VOR/ILS/MB system due to the presence of moisture, dirt, and corrosion between the base and the support of the glide slope antenna and in the electrical connectors of the navigation system. The proposed actions were intended to prevent the display of erroneous or misleading information to the flightcrew in the cockpit due to degradation in the performance of the VOR/ILS/HM system. Since the issuance of that NPRM, we have received new data showing that the degradation in the performance of the VOR/ILS/MB system was not caused by dirt and corrosion affecting the glide slope antenna and certain navigation system connectors. The degraded performance was caused by a parasitic oscillation affecting an internal module of the navigation system, and the navigation system manufacturer has provided service information detailing proven corrective actions. Accordingly, we issued AD 2006–22–05 (71 FR 62907, October 27, 2006), which superseded AD 2003–04–06, amendment 39–13054 (68 FR 8539, February 24, 2003). AD 2006–22–05 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 provides terminating action for the unsafe condition described in AD 2003– 04–06, which was also addressed by the previously mentioned NPRM, Docket No. 2003–NM–67–AD. Therefore, that NPRM is redundant. FAA’s Conclusions Upon further consideration, we have determined that the proposed rule is not necessary. Accordingly, the NPRM is hereby withdrawn. Withdrawal of this NPRM constitutes only such action, and does not preclude the agency from issuing another action in the future, nor does it commit the agency to any course of action in the future. Regulatory Impact Since this action only withdraws a notice of proposed rulemaking, it is neither a proposed nor a final rule and therefore is not covered under Executive Order 12866, the Regulatory Flexibility Act, or DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Withdrawal Accordingly, the notice of proposed rulemaking, Docket 2003–NM–67–AD, published in the Federal Register on March 11, 2004 (69 FR 11549), is withdrawn. Issued in Renton, Washington, on June 13, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–11928 Filed 6–19–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28376; Directorate Identifier 2007–NM–108–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767–200, –300, and –300F Series 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 E:\FR\FM\20JNP1.SGM 20JNP1 rwilkins on PROD1PC63 with PROPOSALS Federal Register / Vol. 72, No. 118 / Wednesday, June 20, 2007 / Proposed Rules certain Boeing Model 767–200, –300, and –300F series airplanes. This proposed AD would require a one-time inspection of each fuel quantity indication system (FQIS) wire harness connector for corrosion of the shield-tobackshell connection, corrosion on the ground jumper, and damage to the ground jumper; a loop resistance test of each FQIS wire harness; and related investigative and corrective actions if necessary. This proposed AD results from reports of corrosion of the out-tank wire harness of the spar connector backshell for the FQIS. We are proposing this AD to detect and correct corrosion of the out-tank wire harness, which could prevent correct grounding of the lightning shield and result in total loss of the electrical grounding between the lightning shield and the airplane structure. This condition, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by August 6, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • 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. • Fax: (202) 493–2251. • Hand Delivery: Room W12–140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., 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: Philip Sheridan, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6441; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments VerDate Aug<31>2005 17:23 Jun 19, 2007 Jkt 211001 regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2007–28376; Directorate Identifier 2007–NM–108–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 http:// 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 http:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647–5527) is located on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion There have been several reports of corrosion of the out-tank wire harness of the spar connector backshell for the fuel quantity indication system (FQIS). Investigations by the airplane manufacturer and the wire harness supplier found that the corrosion was caused by moisture at the connection between the lightning shield, a tinplated copper braid, and the aluminum backshell. The moisture wicked up the copper braid and was trapped between the ferrule and the backshell. Corrosion of the out-tank wire harness, if not detected and corrected, could prevent correct grounding of the lightning shield and result in total loss of the electrical grounding between the lightning shield and the airplane structure. This condition, in combination with flammable fuel vapors, could result in PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 33927 fuel tank explosions and consequent loss of the airplane. Relevant Service Information We have reviewed Boeing Special Attention Service Bulletin 767–28– 0087, dated February 5, 2007. The service bulletin describes procedures for a detailed inspection of each FQIS wire harness connector for corrosion of the shield-to-backshell connection, corrosion on the ground jumper, and damage to the ground jumper. The service bulletin also describes procedures for corrective action if necessary. The corrective action is either upgrading the wire harness by installing a backshell assembly upgrade kit, or replacing the wire harness with a new wire harness that has an improved backshell. The service bulletin also describes procedures for a loop resistance test of each FQIS wire harness, and the following related investigative and corrective actions if necessary. • If the resistance is lower than certain limits specified in the service bulletin, the procedures include a detailed inspection for damage of the wire harness between the spar connector and the wheel well ground terminals; and repair or replacement if necessary. • If the resistance is higher than certain limits specified in the service bulletin, the procedures include doing a joint resistance test of the rear spar ground jumper, and troubleshooting and repairing the ground jumper connection if necessary. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The special attention service bulletin refers to Cinch Service Bulletin CN1156–28–02, Revision C, dated July 31, 2006, as an additional source of service information for installing a backshell assembly upgrade kit and replacing the wire harness. 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 482 airplanes of the affected design in the worldwide fleet. The following table provides the E:\FR\FM\20JNP1.SGM 20JNP1 33928 Federal Register / Vol. 72, No. 118 / Wednesday, June 20, 2007 / Proposed Rules estimated costs for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Action Work hours Detailed inspection ......................................... Loop resistance test ....................................... Average labor rate per hour 1 .................. 2 to 3 ........... $80 $80 $80 ............................ $160 to $240 ............. List of Subjects in 14 CFR Part 39 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. Air transportation, Aircraft, Aviation safety, Safety. Regulatory Findings rwilkins on PROD1PC63 with PROPOSALS Authority for This Rulemaking Comments Due Date (a) The FAA must receive comments on this AD action by August 6, 2007. 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. VerDate Aug<31>2005 17:23 Jun 19, 2007 Jkt 211001 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–2007–28376; Directorate Identifier 2007–NM–108–AD. Applicability (c) This AD applies to Boeing Model 767– 200, –300, and –300F series airplanes, certificated in any category; as identified in Boeing Special Attention Service Bulletin 767–28–0087, dated February 5, 2007. Unsafe Condition (d) This AD results from reports of corrosion of the out-tank wire harness of the spar connector backshell for the fuel quantity indication system (FQIS). We are issuing this AD to detect and correct corrosion of the outtank wire harness, which could prevent correct grounding of the lightning shield and result in total loss of the electrical grounding between the lightning shield and the airplane structure. This condition, in combination with flammable fuel vapors, 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. Frm 00012 202 202 Fleet cost $16,160. $32,320 to $48,480. Inspection, Test, and Related Investigative and Corrective Actions (f) Within 48 months after the effective date of this AD, do the actions in paragraphs (f)(1) and (f)(2) of this AD, and do all applicable related investigative and corrective actions, by accomplishing all the actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–28–0087, dated February 5, 2007. Do all applicable related investigative and corrective actions before further flight. (1) A detailed inspection of each FQIS wire harness connector for corrosion of the shieldto-backshell connection, corrosion on the ground jumper, and damage to the ground jumper. (2) A loop resistance test of each FQIS wire harness. Note 1: Boeing Special Attention Service Bulletin 767–28–0087, dated February 5, 2007, refers to Cinch Service Bulletin CN1156–28–02, Revision C, dated July 31, 2006, as an additional source of service information for installing a backshell assembly upgrade kit, and replacing the wire harness. Alternative Methods of Compliance (AMOCs) Affected ADs (b) None. PO 00000 Number of U.S.-registered airplanes Cost per airplane Fmt 4702 Sfmt 4702 (g)(1) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Issued in Renton, Washington, on June 13, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–11926 Filed 6–19–07; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\20JNP1.SGM 20JNP1

Agencies

[Federal Register Volume 72, Number 118 (Wednesday, June 20, 2007)]
[Proposed Rules]
[Pages 33926-33928]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-11926]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28376; Directorate Identifier 2007-NM-108-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200, -300, and -300F 
Series 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

[[Page 33927]]

certain Boeing Model 767-200, -300, and -300F series airplanes. This 
proposed AD would require a one-time inspection of each fuel quantity 
indication system (FQIS) wire harness connector for corrosion of the 
shield-to-backshell connection, corrosion on the ground jumper, and 
damage to the ground jumper; a loop resistance test of each FQIS wire 
harness; and related investigative and corrective actions if necessary. 
This proposed AD results from reports of corrosion of the out-tank wire 
harness of the spar connector backshell for the FQIS. We are proposing 
this AD to detect and correct corrosion of the out-tank wire harness, 
which could prevent correct grounding of the lightning shield and 
result in total loss of the electrical grounding between the lightning 
shield and the airplane structure. This condition, in combination with 
flammable fuel vapors, could result in fuel tank explosions and 
consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by August 6, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     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.
     Fax: (202) 493-2251.
     Hand Delivery: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue, SE., 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: Philip Sheridan, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6441; 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-
28376; Directorate Identifier 2007-NM-108-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 http://
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 http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://
dms.dot.gov, or in person at the Docket Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
Docket Operations office (telephone (800) 647-5527) is located on the 
ground floor of the West Building at the street address stated in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after the Docket Management System receives them.

Discussion

    There have been several reports of corrosion of the out-tank wire 
harness of the spar connector backshell for the fuel quantity 
indication system (FQIS). Investigations by the airplane manufacturer 
and the wire harness supplier found that the corrosion was caused by 
moisture at the connection between the lightning shield, a tin-plated 
copper braid, and the aluminum backshell. The moisture wicked up the 
copper braid and was trapped between the ferrule and the backshell. 
Corrosion of the out-tank wire harness, if not detected and corrected, 
could prevent correct grounding of the lightning shield and result in 
total loss of the electrical grounding between the lightning shield and 
the airplane structure. This condition, in combination with flammable 
fuel vapors, could result in fuel tank explosions and consequent loss 
of the airplane.

Relevant Service Information

    We have reviewed Boeing Special Attention Service Bulletin 767-28-
0087, dated February 5, 2007. The service bulletin describes procedures 
for a detailed inspection of each FQIS wire harness connector for 
corrosion of the shield-to-backshell connection, corrosion on the 
ground jumper, and damage to the ground jumper. The service bulletin 
also describes procedures for corrective action if necessary. The 
corrective action is either upgrading the wire harness by installing a 
backshell assembly upgrade kit, or replacing the wire harness with a 
new wire harness that has an improved backshell.
    The service bulletin also describes procedures for a loop 
resistance test of each FQIS wire harness, and the following related 
investigative and corrective actions if necessary.
     If the resistance is lower than certain limits specified 
in the service bulletin, the procedures include a detailed inspection 
for damage of the wire harness between the spar connector and the wheel 
well ground terminals; and repair or replacement if necessary.
     If the resistance is higher than certain limits specified 
in the service bulletin, the procedures include doing a joint 
resistance test of the rear spar ground jumper, and troubleshooting and 
repairing the ground jumper connection if necessary.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.
    The special attention service bulletin refers to Cinch Service 
Bulletin CN1156-28-02, Revision C, dated July 31, 2006, as an 
additional source of service information for installing a backshell 
assembly upgrade kit and replacing the wire harness.

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 482 airplanes of the affected design in the 
worldwide fleet. The following table provides the

[[Page 33928]]

estimated costs for U.S. operators to comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                          Number of U.S.-
              Action                     Work hours        Average labor         Cost per airplane          registered              Fleet cost
                                                           rate per hour                                     airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Detailed inspection..............  1....................             $80  $80...........................             202  $16,160.
Loop resistance test.............  2 to 3...............             $80  $160 to $240..................             202  $32,320 to $48,480.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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-2007-28376; Directorate Identifier 2007-NM-
108-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by August 6, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 767-200, -300, and -300F 
series airplanes, certificated in any category; as identified in 
Boeing Special Attention Service Bulletin 767-28-0087, dated 
February 5, 2007.

Unsafe Condition

    (d) This AD results from reports of corrosion of the out-tank 
wire harness of the spar connector backshell for the fuel quantity 
indication system (FQIS). We are issuing this AD to detect and 
correct corrosion of the out-tank wire harness, which could prevent 
correct grounding of the lightning shield and result in total loss 
of the electrical grounding between the lightning shield and the 
airplane structure. This condition, in combination with flammable 
fuel vapors, 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.

Inspection, Test, and Related Investigative and Corrective Actions

    (f) Within 48 months after the effective date of this AD, do the 
actions in paragraphs (f)(1) and (f)(2) of this AD, and do all 
applicable related investigative and corrective actions, by 
accomplishing all the actions specified in the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 767-28-
0087, dated February 5, 2007. Do all applicable related 
investigative and corrective actions before further flight.
    (1) A detailed inspection of each FQIS wire harness connector 
for corrosion of the shield-to-backshell connection, corrosion on 
the ground jumper, and damage to the ground jumper.
    (2) A loop resistance test of each FQIS wire harness.

    Note 1: Boeing Special Attention Service Bulletin 767-28-0087, 
dated February 5, 2007, refers to Cinch Service Bulletin CN1156-28-
02, Revision C, dated July 31, 2006, as an additional source of 
service information for installing a backshell assembly upgrade kit, 
and replacing the wire harness.

Alternative Methods of Compliance (AMOCs)

    (g)(1) The Manager, Seattle Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

    Issued in Renton, Washington, on June 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-11926 Filed 6-19-07; 8:45 am]
BILLING CODE 4910-13-P