Airworthiness Directives; Boeing Model 767 Airplanes, 5623-5626 [E6-1419]

Download as PDF Federal Register / Vol. 71, No. 22 / Thursday, February 2, 2006 / Proposed Rules 5623 Restatement of Requirements of AD 2004– 23–08 A300–28–6061, Revision 04, dated August 1, 2002. DEPARTMENT OF TRANSPORTATION Inspections (f) Prior to the accumulation of 5,000 total hours’ time-in-service or within 250 hours’ time-in-service after February 8, 2000 (the effective date of AD 99–27–07, (superseded by AD 2004–23–08) amendment 39–11488), whichever occurs later, perform a detailed inspection for damage of the center tank fuel pumps and fuel pump canisters, in accordance with Airbus All Operators Telex (AOT) 28–09, dated November 28, 1998. Repeat the inspection prior to the accumulation of 12,000 total hours’ time-inservice, or within 250 hours’ time-in-service after accomplishment of the initial inspection, whichever occurs later. Thereafter, repeat the inspection at intervals not to exceed 250 hours’ time-in-service, until accomplishment of the initial inspection required by paragraph (g) of this AD. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Modification Federal Aviation Administration (i) Within 18 months after December 20, 2004 (the effective date of AD 2004–23–08): Modify the canisters of the center tank fuel pumps (including an operational test) by doing all the actions in accordance with paragraphs 3.A., 3.B., 3.C., and 3.D. of the Accomplishment Instructions of Airbus Service Bulletin A300–28–6069, dated September 4, 2001; Revision 01, dated May 28, 2002; or Revision 02, dated October 17, 2003. After the effective date of this AD, Revision 02 of the service bulletin must be used for accomplishing the modification. Accomplishing this modification ends the repetitive inspections required by paragraph (g) of this AD. 14 CFR Part 39 hsrobinson on PROD1PC71 with PROPOSALS (g) At the applicable time specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Perform a detailed inspection to detect damage of the center tank fuel pumps and perform an eddy current inspection to detect damage of the fuel pump canisters, in accordance with Airbus Alert Service Bulletin A300–28A6061, dated February 19, 1999; or Airbus Service Bulletin A300–28– 6061, Revision 04, dated August 1, 2002. Repeat the inspections thereafter at intervals not to exceed 1,500 flight cycles, until accomplishment of paragraph (i) of this AD. Accomplishment of the inspection required by this paragraph constitutes terminating action for the requirements of paragraph (f) of this AD. (1) For airplanes that have accumulated 11,000 or more total flight cycles as of February 8, 2000: Inspect within 300 flight cycles after February 8, 2000. (2) For airplanes that have accumulated 8,500 or more total flight cycles, but fewer than 11,000 total flight cycles, as of February 8, 2000: Inspect within 750 flight cycles after February 8, 2000. (3) For airplanes that have accumulated fewer than 8,500 total flight cycles as of February 8, 2000: Inspect prior to the accumulation of 7,000 flight cycles, or within 1,500 flight cycles after February 8, 2000, whichever occurs later. Corrective Action (h) If any damage is detected during any inspection required by this AD, prior to further flight, replace the damaged fuel pump or fuel pump canister with a new or serviceable part in accordance with Airbus Alert Service Bulletin A300–28A6061, dated February 19, 1999; or Airbus Service Bulletin VerDate Aug<31>2005 15:25 Feb 01, 2006 Jkt 208001 New Requirements of This AD One-Time Inspection/Replacement if Necessary (j) For airplanes on which Airbus Service Bulletin A300–28–6069, dated September 4, 2001, or Revision 01, dated May 28, 2002, has been accomplished before the effective date of this AD: Within 18 months after the effective date of this AD, perform a one-time detailed inspection of the attachment bolts of the outlet flange of the canisters of the center tank fuel pumps for bolts that are too short and do not protrude through the nut, and replace the bolts as applicable, by doing all the actions in accordance with paragraphs 3.A., 3.B., 3.C., 3.D., and 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A300–28–6087, dated April 8, 2005. Do any applicable bolt replacement before further flight. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (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. (3) AMOCs approved previously in accordance with AD 2004–23–08 are approved as AMOCs for the corresponding provisions of this AD. Related Information (l) French airworthiness directive F–2005– 147, dated August 17, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on January 25, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–1418 Filed 2–1–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 [Docket No. FAA–2006–23762; Directorate Identifier 2005–NM–226–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 all Boeing Model 767 airplanes. This proposed AD would require repetitive inspections for cracking in the skin, the bulkhead outer chord, and the strap of the bulkhead outer chord at station (STA) 1725.5; and repair if necessary. This proposed AD also provides for repairs, which are optional for airplanes on which no cracking is found, that terminate certain inspections. This proposed AD results from reports of cracking in the skin panel common to stringer 7R and aft of the STA 1725.5 butt splice, and in the strap of the bulkhead outer chord at STA 1725.5. We are proposing this AD to detect and correct cracking in the skin, the bulkhead outer chord, or the strap of the bulkhead outer chord in this area, which could progress into surrounding areas and result in reduced structural integrity of the support structure for the vertical or horizontal stabilizer and subsequent loss of control of the airplane. We must receive comments on this proposed AD by March 20, 2006. 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: 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. DATES: E:\FR\FM\02FEP1.SGM 02FEP1 5624 Federal Register / Vol. 71, No. 22 / Thursday, February 2, 2006 / Proposed Rules 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: Candice Gerretsen, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6428; 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–2006–23762; Directorate Identifier 2005–NM–226–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. hsrobinson on PROD1PC71 with PROPOSALS Examining the Docket You may examine the AD docket on the Internet at http://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 VerDate Aug<31>2005 15:25 Feb 01, 2006 Jkt 208001 section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We have received several reports indicating that cracking has been found in the skin panel common to stringer 7R and aft of the station (STA) 1725.5 butt splice, and in the bulkhead outer chord strap at STA 1725.5, on several Boeing Model 767 airplanes. The cracking in the skin panel was found on airplanes that had accumulated between 13,342 and 35,641 total flight cycles. Similar cracking was found during fatigue tests of Model 767 airplanes. The cracking in the bulkhead outer chord strap originated at a fastener hole above stringer 7R in the same area where the skin cracking was found. Cracking in these areas, if not corrected, could progress into surrounding areas and result in reduced structural integrity of the support structure for the vertical or horizontal stabilizer and subsequent loss of control of the airplane. Relevant Service Information We have reviewed Boeing Special Attention Service Bulletin 767–53– 0118, dated September 8, 2005. The service bulletin describes procedures for the following repetitive inspections for cracking: • Part 1: Detailed external inspections of the skin aft of STA 1725.5, between stringers 6R and 8R. • Part 2: Detailed inspections of the bulkhead outer chord and the strap of the bulkhead outer chord, and surface high frequency eddy current (HFEC) inspections of the strap of the bulkhead outer chord at STA 1725.5. The service bulletin refers to the structural repair manual (SRM) for procedures for repairing any crack found in the skin or the strap of the bulkhead outer chord. If cracking is found in the bulkhead outer chord, the service bulletin specifies to contact Boeing for repair procedures. The service bulletin specifies that repairing per a certain procedure in the SRM eliminates the need to continue the Part 1 inspections. The service bulletin also specifies that repairing per certain other procedures in the SRM eliminates the need to continue the Part 1 and Part 2 inspections. The service bulletin specifies a compliance time of 15,000 total flight PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 cycles or 3,000 flight cycles after the original issue date on the service bulletin for performing the initial Part 1 and Part 2 inspections. The service bulletin specifies a repetitive interval not to exceed 6,000 flight cycles for the Part 1 and Part 2 inspections. Any cracking must be repaired before further flight. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. 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, except as discussed under ‘‘Differences Between the Proposed AD and Service Information.’’ Differences Between the Proposed AD and Service Information The service bulletin specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: • Using a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization whom we have authorized to make those findings. The service bulletin specifies compliance times relative to the date of issuance of the service bulletin; however, this proposed AD would require compliance before the specified compliance time after the effective date of this AD. These differences have been coordinated with Boeing. Costs of Compliance There are about 905 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. E:\FR\FM\02FEP1.SGM 02FEP1 Federal Register / Vol. 71, No. 22 / Thursday, February 2, 2006 / Proposed Rules 5625 ESTIMATED COSTS Action Work hours Part 1 Inspection, per inspection cycle. Part 2 Inspections, per inspection cycle. Fleet cost $325, per inspection cycle ........ 387 $125,775, per inspection cycle. 9 65 $585, per inspection cycle ........ 387 $226,395, per inspection cycle. Regulatory Findings hsrobinson on PROD1PC71 with PROPOSALS Number of U.S.-registered airplanes $65 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. 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. 15:25 Feb 01, 2006 Cost per airplane 5 Authority for This Rulemaking VerDate Aug<31>2005 Average labor rate per hour Jkt 208001 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–2006–23762; Directorate Identifier 2005–NM–226–AD. Comments Due Date (a) The FAA must receive comments on this AD action by March 20, 2006. Affected ADs (b) None. Applicability (c) This AD applies to all Boeing Model 767–200, –300, –300F, and –400ER series airplanes, certificated in any category. Unsafe Condition (d) This AD results from reports of cracking in the skin panel common to stringer 7R and aft of the station (STA) 1725.5 butt splice, and in the strap of the bulkhead outer chord at STA 1725.5. We are issuing this AD to detect and correct cracking in the skin, the bulkhead outer chord, or the strap of the bulkhead outer chord in this area, which could progress into surrounding areas and result in reduced structural integrity of the support structure for the vertical or horizontal stabilizer and subsequent loss of control 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. Repetitive Inspections (f) Perform repetitive detailed and high frequency eddy current inspections for PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 cracking in the skin, the bulkhead outer chord, and the strap of the bulkhead outer chord at STA 1725.5, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–53– 0118, dated September 8, 2005. Do the initial and repetitive Part I and Part 2 inspections at the times specified in paragraph 1.E., Compliance, of the service bulletin; except, where the service bulletin specifies a compliance time after the issuance of the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. Repair (g) If any cracking is found during any inspection required by paragraph (f) of this AD: Before further flight, perform applicable repairs in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–53– 0118, dated September 8, 2005; except, where the service bulletin specifies to contact Boeing for repair instructions, before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (i) of this AD. Optional Terminating Action (h) Completing repairs specified in the Accomplishment Instructions of the service bulletin terminates repetitive inspections required by paragraph (f) of this AD as specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Completing repairs specified in paragraph 3.B.3.a. of the service bulletin terminates both the Part 1 and Part 2 inspections required by paragraph (f) of this AD. (2) Completing repairs specified in paragraph 3.B.4.a. of the service bulletin terminates the Part 1 inspections required by paragraph (f) of this AD. Part 2 inspections must continue as required by paragraph (f) of this AD until the repairs specified in paragraph 3.B.3.a. of the service bulletin are completed. Alternative Methods of Compliance (AMOCs) (i)(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. (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. E:\FR\FM\02FEP1.SGM 02FEP1 5626 Federal Register / Vol. 71, No. 22 / Thursday, February 2, 2006 / Proposed Rules (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. 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. [Docket No. FAA–2006–23739; Directorate Identifier 2005–NM–240–AD] 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 Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Comments Invited Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP Airplanes 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–2006–23739; Directorate Identifier 2005–NM–240–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 the 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. EMBRAER has issued Service Bulletin 145–71–0008, Change 01, dated July 24, 2001. The service bulletin describes procedures for modifying the routing of wire harness W407 near the fire extinguishing tube in the rear part of the left-hand and right-hand engines, and installing new supports for derivations of wire harness W407 that lead to certain connectors. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DAC mandated the service information and issued Brazilian airworthiness directive 2005–10–05, dated November 17, 2005, to ensure the continued airworthiness of these airplanes in Brazil. Issued in Renton, Washington, on January 26, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–1419 Filed 2–1–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). hsrobinson on PROD1PC71 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain EMBRAER Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. This proposed AD would require modifying the routing of wire harness W407 near the fire extinguishing tube in the area of each engine, and installing new supports for related wiring. This proposed AD results from reports of chafing of wire harness W407 against the supports and nacelle structure in the engine area. We are proposing this AD to prevent such chafing, which could result in an engine shutting down during flight. DATES: We must receive comments on this proposed AD by March 6, 2006. 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 VerDate Aug<31>2005 15:25 Feb 01, 2006 Jkt 208001 Examining the Docket You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Discussion The Departmento de Aviacao Civil (DAC), which is the airworthiness authority for Brazil, notified us that an unsafe condition may exist on certain EMBRAER Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. The DAC advises that it has received reports of chafing of wire harness W407 against the supports and nacelle structure in the engine area. This condition, if not corrected, could result in an engine shutting down during flight. Relevant Service Information FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in Brazil and are type certificated for operation in the United States under the provisions of § 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DAC has kept the FAA informed of the situation described above. We have examined the DAC’s findings, evaluated all pertinent information, and determined that we need to issue an AD for airplanes of this type design that are certificated for operation in the United States. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously. E:\FR\FM\02FEP1.SGM 02FEP1

Agencies

[Federal Register Volume 71, Number 22 (Thursday, February 2, 2006)]
[Proposed Rules]
[Pages 5623-5626]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-1419]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23762; Directorate Identifier 2005-NM-226-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 all Boeing Model 767 airplanes. This proposed AD would require 
repetitive inspections for cracking in the skin, the bulkhead outer 
chord, and the strap of the bulkhead outer chord at station (STA) 
1725.5; and repair if necessary. This proposed AD also provides for 
repairs, which are optional for airplanes on which no cracking is 
found, that terminate certain inspections. This proposed AD results 
from reports of cracking in the skin panel common to stringer 7R and 
aft of the STA 1725.5 butt splice, and in the strap of the bulkhead 
outer chord at STA 1725.5. We are proposing this AD to detect and 
correct cracking in the skin, the bulkhead outer chord, or the strap of 
the bulkhead outer chord in this area, which could progress into 
surrounding areas and result in reduced structural integrity of the 
support structure for the vertical or horizontal stabilizer and 
subsequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by March 20, 2006.

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: 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.

[[Page 5624]]

    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: Candice Gerretsen, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6428; 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-2006-
23762; Directorate Identifier 2005-NM-226-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 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

    We have received several reports indicating that cracking has been 
found in the skin panel common to stringer 7R and aft of the station 
(STA) 1725.5 butt splice, and in the bulkhead outer chord strap at STA 
1725.5, on several Boeing Model 767 airplanes. The cracking in the skin 
panel was found on airplanes that had accumulated between 13,342 and 
35,641 total flight cycles. Similar cracking was found during fatigue 
tests of Model 767 airplanes. The cracking in the bulkhead outer chord 
strap originated at a fastener hole above stringer 7R in the same area 
where the skin cracking was found. Cracking in these areas, if not 
corrected, could progress into surrounding areas and result in reduced 
structural integrity of the support structure for the vertical or 
horizontal stabilizer and subsequent loss of control of the airplane.

Relevant Service Information

    We have reviewed Boeing Special Attention Service Bulletin 767-53-
0118, dated September 8, 2005. The service bulletin describes 
procedures for the following repetitive inspections for cracking:
     Part 1: Detailed external inspections of the skin aft of 
STA 1725.5, between stringers 6R and 8R.
     Part 2: Detailed inspections of the bulkhead outer chord 
and the strap of the bulkhead outer chord, and surface high frequency 
eddy current (HFEC) inspections of the strap of the bulkhead outer 
chord at STA 1725.5.
    The service bulletin refers to the structural repair manual (SRM) 
for procedures for repairing any crack found in the skin or the strap 
of the bulkhead outer chord. If cracking is found in the bulkhead outer 
chord, the service bulletin specifies to contact Boeing for repair 
procedures. The service bulletin specifies that repairing per a certain 
procedure in the SRM eliminates the need to continue the Part 1 
inspections. The service bulletin also specifies that repairing per 
certain other procedures in the SRM eliminates the need to continue the 
Part 1 and Part 2 inspections.
    The service bulletin specifies a compliance time of 15,000 total 
flight cycles or 3,000 flight cycles after the original issue date on 
the service bulletin for performing the initial Part 1 and Part 2 
inspections. The service bulletin specifies a repetitive interval not 
to exceed 6,000 flight cycles for the Part 1 and Part 2 inspections. 
Any cracking must be repaired before further flight.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

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, except as discussed under 
``Differences Between the Proposed AD and Service Information.''

Differences Between the Proposed AD and Service Information

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Commercial Airplanes Delegation Option Authorization 
Organization whom we have authorized to make those findings.
    The service bulletin specifies compliance times relative to the 
date of issuance of the service bulletin; however, this proposed AD 
would require compliance before the specified compliance time after the 
effective date of this AD.
    These differences have been coordinated with Boeing.

Costs of Compliance

    There are about 905 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.

[[Page 5625]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of
                                                 Average                            U.S.-
             Action                Work hours   labor rate   Cost per  airplane   registered      Fleet cost
                                                 per hour                         airplanes
----------------------------------------------------------------------------------------------------------------
Part 1 Inspection, per                      5          $65  $325, per                    387  $125,775, per
 inspection cycle.                                           inspection cycle.                 inspection cycle.
Part 2 Inspections, per                     9           65  $585, per                    387  $226,395, per
 inspection cycle.                                           inspection cycle.                 inspection cycle.
----------------------------------------------------------------------------------------------------------------

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-2006-23762; Directorate Identifier 2005-NM-
226-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by March 20, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Boeing Model 767-200, -300, -300F, 
and -400ER series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from reports of cracking in the skin panel 
common to stringer 7R and aft of the station (STA) 1725.5 butt 
splice, and in the strap of the bulkhead outer chord at STA 1725.5. 
We are issuing this AD to detect and correct cracking in the skin, 
the bulkhead outer chord, or the strap of the bulkhead outer chord 
in this area, which could progress into surrounding areas and result 
in reduced structural integrity of the support structure for the 
vertical or horizontal stabilizer and subsequent loss of control 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.

Repetitive Inspections

    (f) Perform repetitive detailed and high frequency eddy current 
inspections for cracking in the skin, the bulkhead outer chord, and 
the strap of the bulkhead outer chord at STA 1725.5, in accordance 
with the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 767-53-0118, dated September 8, 2005. Do the 
initial and repetitive Part I and Part 2 inspections at the times 
specified in paragraph 1.E., Compliance, of the service bulletin; 
except, where the service bulletin specifies a compliance time after 
the issuance of the service bulletin, this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.

Repair

    (g) If any cracking is found during any inspection required by 
paragraph (f) of this AD: Before further flight, perform applicable 
repairs in accordance with the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 767-53-0118, dated September 8, 
2005; except, where the service bulletin specifies to contact Boeing 
for repair instructions, before further flight, repair the cracking 
using a method approved in accordance with the procedures specified 
in paragraph (i) of this AD.

Optional Terminating Action

    (h) Completing repairs specified in the Accomplishment 
Instructions of the service bulletin terminates repetitive 
inspections required by paragraph (f) of this AD as specified in 
paragraphs (h)(1) and (h)(2) of this AD.
    (1) Completing repairs specified in paragraph 3.B.3.a. of the 
service bulletin terminates both the Part 1 and Part 2 inspections 
required by paragraph (f) of this AD.
    (2) Completing repairs specified in paragraph 3.B.4.a. of the 
service bulletin terminates the Part 1 inspections required by 
paragraph (f) of this AD. Part 2 inspections must continue as 
required by paragraph (f) of this AD until the repairs specified in 
paragraph 3.B.3.a. of the service bulletin are completed.

Alternative Methods of Compliance (AMOCs)

    (i)(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.
    (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.

[[Page 5626]]

    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.

    Issued in Renton, Washington, on January 26, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-1419 Filed 2-1-06; 8:45 am]
BILLING CODE 4910-13-P