Airworthiness Directives; Boeing Model 767 Airplanes, 56386-56389 [05-19234]

Download as PDF 56386 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules December 7, 2000; or Revision 2, dated October 7, 2004. After the effective date of this AD, only Revision 2 of the service bulletin may be used. (1) If the lubrication passage is not blocked and no fractured bearing or loose or damaged joint is found, do paragraph (h) of this AD. (2) If the lubrication passage is blocked and no fractured bearing or loose or damaged joint is found, repeat the inspection required by paragraph (f) of this AD at intervals not to exceed 60 days, and within 24 months after doing the initial inspection, do the actions required by paragraph (g)(3) of this AD. (3) If any fractured bearing or loose or damaged joint is found, before further flight, do the corrective action (including removal of the link assembly, inspection for damage, and replacement with a new assembly if damaged), as specified in Part 2 of the Accomplishment Instructions of the service bulletin. New Requirements of This AD (h) For airplanes having line numbers 1 through 819 inclusive, on which the lubrication passage has not been found blocked and no fractured bearing or loose or damaged joint has been found, and on which Part 2 of Boeing Alert Service Bulletin 767– 27A0167 has not been done: Within 24 months after the most recent inspection in accordance with paragraph (b)(1) of AD 2002–01–15, remove the link assembly, perform a detailed inspection of the link assembly for damage, and reinstall the undamaged link or replace it with a new link assembly that has been inspected and found to be free of damage or other discrepancy, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767–27A0167, Revision 2, dated October 7, 2004. Detailed Inspection of Bearing Ball and Outer Race (i) For all airplanes: Remove the link assembly, and perform a detailed inspection for cracking of the bearing ball, and for severe wear of the outer race of the bearing, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767–27A0167, Revision 2, dated October 7, 2004. Do this action at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, as applicable. Then, repeat this action at intervals not to exceed 72 months. If any cracking or severe wear is found during any inspection required by this paragraph: Before further flight, do the corrective action in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767–27A0167, Revision 2, dated October 7, 2004, or do paragraph (j) of this AD. (1) For airplanes identified in the service bulletin as being in Group 1: Within 72 months after doing Part 2 of the Accomplishment Instructions of Boeing Service Bulletin 767–27A0167, dated December 7, 2000; or Revision 2, dated October 7, 2004, or within 18 months after the effective date of this AD, whichever is later. (2) For airplanes identified in the service bulletin as being in Group 2: Do the initial VerDate Aug<31>2005 13:24 Sep 26, 2005 Jkt 205001 inspection within 72 months since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness; or within 18 months after the effective date of this AD; whichever is later. Optional Terminating Action (j) For all airplanes: Replacing the existing link assemblies of the trailing edge flaps with new, improved or modified assemblies that contain new bearings, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767–27–0196, dated April 21, 2005, ends the repetitive removal/ inspections required by paragraph (g), (h), and (i) of this AD, as applicable. Actions Accomplished Previously (k) Inspections and corrective actions done before the effective date of this AD in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767–27A0167, Revision 1, dated June 6, 2002, are acceptable for compliance with the corresponding actions required by this AD. No Reporting Requirement (l) Although Boeing Alert Service Bulletin 767–27A0167, Revision 2, dated October 7, 2004, specifies to submit certain information to the manufacturer, this AD does not require that action. Alternative Methods of Compliance (AMOCs) (m)(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) 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. (3) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (4) AMOCs approved previously according to AD 2002–01–15 are approved as AMOCs for the corresponding provisions of this AD. Issued in Renton, Washington, on September 16, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–19233 Filed 9–26–05; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22523; Directorate Identifier 2005–NM–058–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 drilling a drain hole in the flanged tubes for the E1A and E1B elevator control cable aft pressure seals; doing repetitive inspections for dirt, loose particles, or blockage of the flanged tube and drain hole for the E1A and E1B elevator control cable aft pressure seals and corrective action if necessary; replacing the aft air-intake duct assembly with a new or modified aft air-intake duct assembly and installing a dripshield; and modifying the side brace fittings and installing gutters on the horizontal stabilizer center section. This proposed AD results from reports of stiff operation of the elevator pitch control system and jammed elevator controls. We are proposing this AD to prevent moisture from collecting and freezing on the elevator control system components, which could limit the ability of the flightcrew to make elevator control inputs and result in reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by November 14, 2005. 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, ADDRESSES: E:\FR\FM\27SEP1.SGM 27SEP1 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 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: Kelly McGuckin, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6490; 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–2005–22523; Directorate Identifier 2005–NM–058–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. VerDate Aug<31>2005 13:24 Sep 26, 2005 Jkt 205001 Discussion We have received reports of stiff operation of the elevator pitch control system and jammed elevator controls on Model 767 airplanes. One incident involved difficulty in flaring the airplane and resulted in a subsequent hard landing. This incident as well as one other incident was caused by moisture collecting and freezing onto the left elevator cables at the aft pressure bulkhead cable seats. Another incident involved a leaking auxiliary power unit (APU) intake duct seal, which allowed water to collect and freeze onto the linear variable differential transducer (LVDT) for the center elevator autopilot. The manufacturer also determined that water could enter section 48 of the airplane through the stabilizer side of the body fairing panels. These conditions, if not corrected, could limit the ability of the flightcrew to make elevator control inputs and result in reduced controllability of the airplane. Relevant Service Information We have reviewed Boeing Service Bulletin 767–27A0192, Revision 1, dated March 17, 2005 (for Model 767– 200, –300, and –300F series airplanes); and Boeing Alert Service Bulletin 767– 27A0193, dated December 4, 2003 (for Model 767–400ER series airplanes). The service bulletins describe procedures for drilling a drain hole in the flanged tubes for the E1A and E1B elevator control cable aft pressure seals. We have also reviewed Boeing Service Bulletin 767–27–0204, dated January 27, 2005 (for Model 767–200, –300, and –300F series airplanes); and Boeing Service Bulletin 767–27–0205, dated January 27, 2005 (for Model 767–400ER series airplanes). The service bulletins describe procedures for doing repetitive inspections for dirt, loose particles, or blockage of the flanged tube and drain hole for the E1A and E1B elevator control cable aft pressure seals and corrective action if necessary. The corrective action includes cleaning the flanged tube and drain hole. We have also reviewed Boeing Alert Service Bulletin 767–49A0035, Revision 1, dated December 11, 2003 (for certain Model 767–200, –300, and –300F series airplanes). The service bulletin describes procedures for replacing the aft air-intake duct assembly with a new or modified aft air-intake duct assembly and installing a dripshield. We have also reviewed Boeing Alert Service Bulletin 767–51A0027, dated December 9, 2004 (for Model 767–200, –300, and –300F series airplanes); and Boeing Alert Service Bulletin 767– PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 56387 51A0028, dated December 9, 2004 (for Model 767–400ER series airplanes). The service bulletins describe procedures for modifying the side brace fittings and installing gutters on the horizontal stabilizer center section. The modification includes drilling a drain hole, doing a dye penetrant inspection for cracks of the drain hole, and applying certain finishes. 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 Bulletins.’’ Differences Between the Proposed AD and Service Bulletins Boeing Service Bulletin 767–27–0204, dated January 27, 2005; and Boeing Service Bulletin 767–27–0205, dated January 27, 2005; specify an inspection threshold of 24 months after the delivery date of the airplane. However, paragraph (g)(2)(ii) of this proposed AD specifies an inspection threshold of 24 months after the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness. This decision is based on our determination that ‘‘delivery date’’ may be interpreted differently by different operators. We find that our proposed terminology is generally understood within the industry and records will always exist that establish these dates with certainty. Boeing Alert Service Bulletin 767– 51A0027, dated December 9, 2004; and Boeing Alert Service Bulletin 767– 51A0028, dated December 9, 2004; do not specify a corrective action if cracks are found during the dye penetrant inspection for cracks of the drain hole specified in Figure 2 of the service bulletins. This proposed AD would require operators to repair this condition according to a method approved by the FAA. Clarification of Inspection Terminology In this proposed AD, the inspections specified in Boeing Service Bulletin 767–27–0204, dated January 27, 2005; and Boeing Service Bulletin 767–27– E:\FR\FM\27SEP1.SGM 27SEP1 56388 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 0205, dated January 27, 2005; are referred to as a ‘‘detailed inspection.’’ We have included the definition for a detailed inspection in a note in the proposed AD. Costs of Compliance There are about 900 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 410 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. The average labor rate per hour is $65. We estimate that this proposed AD may have a total fleet cost of up to $1,789,953 for the initial inspection and modifications as well as a fleet cost of $26,650 per inspection cycle for the repetitive inspections. ESTIMATED COSTS Work hours Airplanes Action Model 767 airplanes identified in Boeing Service Bulletin 767–27A0192, Revision 1, dated March 17, 2005; and Boeing Alert Service Bulletin 767– 27A0193, dated December 4, 2003. Model 767 airplanes identified in Boeing Service Bulletin 767–27–0204, dated January 27, 2005; and Boeing Service Bulletin 767–27–0205, dated January 27, 2005. Model 767–200, –300, and –300F series airplanes identified in Boeing Alert Service Bulletin 767– 49A0035, Revision 1, dated December 11, 2003. Drain hole addition 2 $0 ....................................... $130. Drain Hole Inspection. 1 $0 ....................................... $65, per inspection cycle. Aft Air-intake Duct Assembly and Dripshield Installation. 4 Model 767 airplanes dentified in Boeing Alert Service Bulletin 767–51A0027, dated December 9, 2004; and Boeing Alert Service Bulletin 767–51A0028, dated December 9, 2004. Gutter Installation 9 $1,462 for rework kit (optional—$18,985 for new assembly used for first replacement to generate a spare assembly). $1,821 ................................ $1,722 with rework kit (optional—$19,245 with new assembly used for first replacement to generate a spare assembly). $2,406. 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: VerDate Aug<31>2005 13:24 Sep 26, 2005 Jkt 205001 Parts 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. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 Cost per airplane Boeing: Docket No. FAA–2005–22523; Directorate Identifier 2005–NM–058–AD. Comments Due Date (a) The FAA must receive comments on this AD action by November 14, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 767– 200, –300, –300F, and –400ER series airplanes, certificated in any category; as identified in Boeing Service Bulletin 767– 27A0192, Revision 1, dated March 17, 2005; Boeing Alert Service Bulletin 767–27A0193, dated December 4, 2003; Boeing Alert Service Bulletin 767–49A0035, Revision 1, dated December 11, 2003; Boeing Service Bulletin 767–27–0204, dated January 27, 2005; Boeing Service Bulletin 767–27–0205, dated January 27, 2005; Boeing Alert Service Bulletin 767– 51A0027, dated December 9, 2004; and Boeing Alert Service Bulletin 767–51A0028, dated December 9, 2004. Unsafe Condition (d) This AD results from reports of stiff operation of the elevator pitch control system and jammed elevator controls. We are issuing this AD to prevent moisture from collecting and freezing on the elevator control system components, which could limit the ability of the flightcrew to make elevator control inputs and result in reduced controllability 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. E:\FR\FM\27SEP1.SGM 27SEP1 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules Inspections, Modifications, Replacements, and Corrective Actions (f) For airplanes identified in Boeing Service Bulletin 767–27A0192, Revision 1, dated March 17, 2005; and Boeing Alert Service Bulletin 767–27A0193, dated December 4, 2003: Within 18 months after the effective date of this AD, drill a drain hole in the flanged tubes for the E1A and E1B elevator control cable aft pressure seals by doing all the actions specified in the Accomplishment Instructions of Boeing Service Bulletin 767–727A0192, Revision 1, dated March 17, 2005 (for Model 767–200, –300, and –300F series airplanes); and Boeing Alert Service Bulletin 767–27A00193, dated December 4, 2003 (for Model 767– 400ER series airplanes); as applicable. (g) For airplanes identified in Boeing Service Bulletin 767–27–0204, dated January 27, 2005; and Boeing Service Bulletin 767– 27–0205, dated January 27, 2005: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, do a detailed inspection for dirt, loose particles, or blockage of the flanged tube and drain hole for the E1A and E1B elevator control cable aft pressure seals, and any applicable corrective action, by doing all the actions specified in the Accomplishment Instructions of Boeing Service Bulletin 767–27–0204, dated January 27, 2005 (for Model 767–200, –300, and –300F series airplanes); and Boeing Service Bulletin 767–27–0205, dated January 27, 2005 (for Model 767–400ER series airplanes); as applicable. Do any applicable corrective actions before further flight. Repeat the detailed inspection thereafter at intervals not to exceed 24 months. (1) For airplanes identified in paragraph (g) that are also identified in paragraph (f) of this AD: Do the inspection at the time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD, whichever occurs later. (i) Within 24 months after doing the actions required by paragraph (f) of this AD. (ii) Within 24 months after the effective date of this AD. (2) For airplanes identified in paragraph (g) that are not identified in paragraph (f) of this AD: Do the inspection at the time specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, whichever occurs later. (i) Within 24 months after the effective date of this AD. (ii) Within 24 months since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness. 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.’’ (h) For airplanes identified in Boeing Alert Service Bulletin 767–49A0035, Revision 1, dated December 11, 2003: Within 18 months after the effective date of this AD, replace the VerDate Aug<31>2005 13:24 Sep 26, 2005 Jkt 205001 aft air-intake duct assembly with a new or modified aft air-intake duct assembly and install a dripshield by doing all the actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 767–49A0035, Revision 1, dated December 11, 2003. (i) For airplanes identified in Boeing Alert Service Bulletin 767–51A0027, dated December 9, 2004; and Boeing Alert Service Bulletin 767–51A0028, dated December 9, 2004: Within 60 months after the effective date of this AD, modify the side brace fittings and install gutters on the horizontal stabilizer center section, by doing all the actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 767–51A0027, dated December 9, 2004 (for Model 767–200, –300, and –300F series airplanes); and Boeing Alert Service Bulletin 767–51A0028, dated December 9, 2004 (for Model 767–400ER series airplanes); as applicable; except if cracks are found during the dye penetrant inspection specified in Figure 2 of the service bulletins, this AD requires, before further flight, operators to repair this condition according to a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD. Actions Accomplished According to Previous Issue of Service Bulletin (j) Actions accomplished before the effective date of this AD according to Boeing Alert Service Bulletin 767–27A0192, dated December 4, 2003, are considered acceptable for compliance with the corresponding actions specified in this AD. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Seattle 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 14 CFR 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 September 16, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–19234 Filed 9–26–05; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 56389 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22524; Directorate Identifier 2005–NM–135–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200, A330–300, A340–200, and A340–300 Series Airplanes, and Model A340–541 and A340–642 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 Airbus Model A330–200, A330– 300, A340–200, and A340–300 series airplanes, and A340–541 and A340–642 airplanes. This proposed AD would require inspecting to determine if certain emergency escape slides/slide rafts (referred to as slide/rafts) are installed in certain crew/passenger doors; and, if so, performing a one-time inspection to determine if the electrical harnesses of the slide/rafts are properly routed, and rerouting the harnesses if necessary. This proposed AD results from a report that a slide/raft failed to deploy properly during a deployment test. We are proposing this AD to detect and correct improper routing of the electrical harnesses of certain slide/ rafts, which could prevent proper deployment of the slide/rafts and delay evacuation of passengers and flightcrew during an emergency. DATES: We must receive comments on this proposed AD by October 27, 2005. 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. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, E:\FR\FM\27SEP1.SGM 27SEP1

Agencies

[Federal Register Volume 70, Number 186 (Tuesday, September 27, 2005)]
[Proposed Rules]
[Pages 56386-56389]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-19234]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22523; Directorate Identifier 2005-NM-058-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 
drilling a drain hole in the flanged tubes for the E1A and E1B elevator 
control cable aft pressure seals; doing repetitive inspections for 
dirt, loose particles, or blockage of the flanged tube and drain hole 
for the E1A and E1B elevator control cable aft pressure seals and 
corrective action if necessary; replacing the aft air-intake duct 
assembly with a new or modified aft air-intake duct assembly and 
installing a dripshield; and modifying the side brace fittings and 
installing gutters on the horizontal stabilizer center section. This 
proposed AD results from reports of stiff operation of the elevator 
pitch control system and jammed elevator controls. We are proposing 
this AD to prevent moisture from collecting and freezing on the 
elevator control system components, which could limit the ability of 
the flightcrew to make elevator control inputs and result in reduced 
controllability of the airplane.

DATES: We must receive comments on this proposed AD by November 14, 
2005.

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,

[[Page 56387]]

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: Kelly McGuckin, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 917-6490; 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-2005-
22523; Directorate Identifier 2005-NM-058-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 reports of stiff operation of the elevator pitch 
control system and jammed elevator controls on Model 767 airplanes. One 
incident involved difficulty in flaring the airplane and resulted in a 
subsequent hard landing. This incident as well as one other incident 
was caused by moisture collecting and freezing onto the left elevator 
cables at the aft pressure bulkhead cable seats. Another incident 
involved a leaking auxiliary power unit (APU) intake duct seal, which 
allowed water to collect and freeze onto the linear variable 
differential transducer (LVDT) for the center elevator autopilot. The 
manufacturer also determined that water could enter section 48 of the 
airplane through the stabilizer side of the body fairing panels. These 
conditions, if not corrected, could limit the ability of the flightcrew 
to make elevator control inputs and result in reduced controllability 
of the airplane.

Relevant Service Information

    We have reviewed Boeing Service Bulletin 767-27A0192, Revision 1, 
dated March 17, 2005 (for Model 767-200, -300, and -300F series 
airplanes); and Boeing Alert Service Bulletin 767-27A0193, dated 
December 4, 2003 (for Model 767-400ER series airplanes). The service 
bulletins describe procedures for drilling a drain hole in the flanged 
tubes for the E1A and E1B elevator control cable aft pressure seals.
    We have also reviewed Boeing Service Bulletin 767-27-0204, dated 
January 27, 2005 (for Model 767-200, -300, and -300F series airplanes); 
and Boeing Service Bulletin 767-27-0205, dated January 27, 2005 (for 
Model 767-400ER series airplanes). The service bulletins describe 
procedures for doing repetitive inspections for dirt, loose particles, 
or blockage of the flanged tube and drain hole for the E1A and E1B 
elevator control cable aft pressure seals and corrective action if 
necessary. The corrective action includes cleaning the flanged tube and 
drain hole.
    We have also reviewed Boeing Alert Service Bulletin 767-49A0035, 
Revision 1, dated December 11, 2003 (for certain Model 767-200, -300, 
and -300F series airplanes). The service bulletin describes procedures 
for replacing the aft air-intake duct assembly with a new or modified 
aft air-intake duct assembly and installing a dripshield.
    We have also reviewed Boeing Alert Service Bulletin 767-51A0027, 
dated December 9, 2004 (for Model 767-200, -300, and -300F series 
airplanes); and Boeing Alert Service Bulletin 767-51A0028, dated 
December 9, 2004 (for Model 767-400ER series airplanes). The service 
bulletins describe procedures for modifying the side brace fittings and 
installing gutters on the horizontal stabilizer center section. The 
modification includes drilling a drain hole, doing a dye penetrant 
inspection for cracks of the drain hole, and applying certain finishes.
    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 Bulletins.''

Differences Between the Proposed AD and Service Bulletins

    Boeing Service Bulletin 767-27-0204, dated January 27, 2005; and 
Boeing Service Bulletin 767-27-0205, dated January 27, 2005; specify an 
inspection threshold of 24 months after the delivery date of the 
airplane. However, paragraph (g)(2)(ii) of this proposed AD specifies 
an inspection threshold of 24 months after the date of issuance of the 
original standard airworthiness certificate or the date of issuance of 
the original export certificate of airworthiness. This decision is 
based on our determination that ``delivery date'' may be interpreted 
differently by different operators. We find that our proposed 
terminology is generally understood within the industry and records 
will always exist that establish these dates with certainty.
    Boeing Alert Service Bulletin 767-51A0027, dated December 9, 2004; 
and Boeing Alert Service Bulletin 767-51A0028, dated December 9, 2004; 
do not specify a corrective action if cracks are found during the dye 
penetrant inspection for cracks of the drain hole specified in Figure 2 
of the service bulletins. This proposed AD would require operators to 
repair this condition according to a method approved by the FAA.

Clarification of Inspection Terminology

    In this proposed AD, the inspections specified in Boeing Service 
Bulletin 767-27-0204, dated January 27, 2005; and Boeing Service 
Bulletin 767-27-

[[Page 56388]]

0205, dated January 27, 2005; are referred to as a ``detailed 
inspection.'' We have included the definition for a detailed inspection 
in a note in the proposed AD.

Costs of Compliance

    There are about 900 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 410 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD. The average labor rate 
per hour is $65. We estimate that this proposed AD may have a total 
fleet cost of up to $1,789,953 for the initial inspection and 
modifications as well as a fleet cost of $26,650 per inspection cycle 
for the repetitive inspections.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                             Work
             Airplanes                       Action          hours          Parts            Cost per airplane
----------------------------------------------------------------------------------------------------------------
Model 767 airplanes identified in    Drain hole addition..       2  $0...................  $130.
 Boeing Service Bulletin 767-
 27A0192, Revision 1, dated March
 17, 2005; and Boeing Alert Service
 Bulletin 767-27A0193, dated
 December 4, 2003.
Model 767 airplanes identified in    Drain Hole Inspection       1  $0...................  $65, per inspection
 Boeing Service Bulletin 767-27-                                                            cycle.
 0204, dated January 27, 2005; and
 Boeing Service Bulletin 767-27-
 0205, dated January 27, 2005.
Model 767-200, -300, and -300F       Aft Air-intake Duct         4  $1,462 for rework kit  $1,722 with rework
 series airplanes identified in       Assembly and                   (optional--$18,985     kit (optional--
 Boeing Alert Service Bulletin 767-   Dripshield                     for new assembly       $19,245 with new
 49A0035, Revision 1, dated           Installation.                  used for first         assembly used for
 December 11, 2003.                                                  replacement to         first replacement to
                                                                     generate a spare       generate a spare
                                                                     assembly).             assembly).
Model 767 airplanes dentified in     Gutter Installation..       9  $1,821...............  $2,406.
 Boeing Alert Service Bulletin 767-
 51A0027, dated December 9, 2004;
 and Boeing Alert Service Bulletin
 767-51A0028, dated December 9,
 2004.
----------------------------------------------------------------------------------------------------------------

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-2005-22523; Directorate Identifier 2005-NM-
058-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by November 
14, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 767-200, -300, -300F, and -
400ER series airplanes, certificated in any category; as identified 
in Boeing Service Bulletin 767-27A0192, Revision 1, dated March 17, 
2005; Boeing Alert Service Bulletin 767-27A0193, dated December 4, 
2003; Boeing Alert Service Bulletin 767-49A0035, Revision 1, dated 
December 11, 2003; Boeing Service Bulletin 767-27-0204, dated 
January 27, 2005; Boeing Service Bulletin 767-27-0205, dated January 
27, 2005; Boeing Alert Service Bulletin 767-51A0027, dated December 
9, 2004; and Boeing Alert Service Bulletin 767-51A0028, dated 
December 9, 2004.

Unsafe Condition

    (d) This AD results from reports of stiff operation of the 
elevator pitch control system and jammed elevator controls. We are 
issuing this AD to prevent moisture from collecting and freezing on 
the elevator control system components, which could limit the 
ability of the flightcrew to make elevator control inputs and result 
in reduced controllability 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.

[[Page 56389]]

Inspections, Modifications, Replacements, and Corrective Actions

    (f) For airplanes identified in Boeing Service Bulletin 767-
27A0192, Revision 1, dated March 17, 2005; and Boeing Alert Service 
Bulletin 767-27A0193, dated December 4, 2003: Within 18 months after 
the effective date of this AD, drill a drain hole in the flanged 
tubes for the E1A and E1B elevator control cable aft pressure seals 
by doing all the actions specified in the Accomplishment 
Instructions of Boeing Service Bulletin 767-727A0192, Revision 1, 
dated March 17, 2005 (for Model 767-200, -300, and -300F series 
airplanes); and Boeing Alert Service Bulletin 767-27A00193, dated 
December 4, 2003 (for Model 767-400ER series airplanes); as 
applicable.
    (g) For airplanes identified in Boeing Service Bulletin 767-27-
0204, dated January 27, 2005; and Boeing Service Bulletin 767-27-
0205, dated January 27, 2005: At the applicable time specified in 
paragraph (g)(1) or (g)(2) of this AD, do a detailed inspection for 
dirt, loose particles, or blockage of the flanged tube and drain 
hole for the E1A and E1B elevator control cable aft pressure seals, 
and any applicable corrective action, by doing all the actions 
specified in the Accomplishment Instructions of Boeing Service 
Bulletin 767-27-0204, dated January 27, 2005 (for Model 767-200, -
300, and -300F series airplanes); and Boeing Service Bulletin 767-
27-0205, dated January 27, 2005 (for Model 767-400ER series 
airplanes); as applicable. Do any applicable corrective actions 
before further flight. Repeat the detailed inspection thereafter at 
intervals not to exceed 24 months.
    (1) For airplanes identified in paragraph (g) that are also 
identified in paragraph (f) of this AD: Do the inspection at the 
time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD, 
whichever occurs later.
    (i) Within 24 months after doing the actions required by 
paragraph (f) of this AD.
    (ii) Within 24 months after the effective date of this AD.
    (2) For airplanes identified in paragraph (g) that are not 
identified in paragraph (f) of this AD: Do the inspection at the 
time specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, 
whichever occurs later.
    (i) Within 24 months after the effective date of this AD.
    (ii) Within 24 months since the date of issuance of the original 
standard airworthiness certificate or the date of issuance of the 
original export certificate of airworthiness.

    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.''

    (h) For airplanes identified in Boeing Alert Service Bulletin 
767-49A0035, Revision 1, dated December 11, 2003: Within 18 months 
after the effective date of this AD, replace the aft air-intake duct 
assembly with a new or modified aft air-intake duct assembly and 
install a dripshield by doing all the actions specified in the 
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
49A0035, Revision 1, dated December 11, 2003.
    (i) For airplanes identified in Boeing Alert Service Bulletin 
767-51A0027, dated December 9, 2004; and Boeing Alert Service 
Bulletin 767-51A0028, dated December 9, 2004: Within 60 months after 
the effective date of this AD, modify the side brace fittings and 
install gutters on the horizontal stabilizer center section, by 
doing all the actions specified in the Accomplishment Instructions 
of Boeing Alert Service Bulletin 767-51A0027, dated December 9, 2004 
(for Model 767-200, -300, and -300F series airplanes); and Boeing 
Alert Service Bulletin 767-51A0028, dated December 9, 2004 (for 
Model 767-400ER series airplanes); as applicable; except if cracks 
are found during the dye penetrant inspection specified in Figure 2 
of the service bulletins, this AD requires, before further flight, 
operators to repair this condition according to a method approved by 
the Manager, Seattle Aircraft Certification Office (ACO), FAA. For a 
repair method to be approved by the Manager, Seattle ACO, as 
required by this paragraph, the Manager's approval letter must 
specifically refer to this AD.

Actions Accomplished According to Previous Issue of Service Bulletin

    (j) Actions accomplished before the effective date of this AD 
according to Boeing Alert Service Bulletin 767-27A0192, dated 
December 4, 2003, are considered acceptable for compliance with the 
corresponding actions specified in this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle 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 14 CFR 
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 September 16, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-19234 Filed 9-26-05; 8:45 am]
BILLING CODE 4910-13-P