Airworthiness Directives; Boeing Model 767 Series Airplanes Powered by General Electric or Pratt & Whitney Engines, 32527-32534 [05-11050]

Download as PDF Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules 32527 TABLE 1.—COMPLIANCE TIMES—Continued Applicable airplanes Initial inspection Repetitive inspections Model 777–200 and –300 airplanes powered by Rolls Royce engines, L/Ns 298 and subsequent. Before the accumulation of 5,000 total flight cycles or within 750 days after the effective date of this AD, whichever is later. At intervals not to exceed 5,000 flight cycles or 750 days, whichever is later. Concurrent Actions for Certain Airplanes (g) For Model 777–200 series airplanes identified in Boeing Service Bulletin 777–27– 0009, Revision 1, dated May 8, 2003: Before or concurrently with accomplishing paragraph (f) of this AD, replace the yoke assemblies and pins of the left inboard, left outboard, right inboard, and right outboard flaperon PCUs with new, improved yoke assemblies and pins by doing all of the actions specified in the Accomplishment Instructions of Boeing Service Bulletin 777– 27–0009, Revision 1, dated May 8, 2003; except where the service bulletin specifies installing yoke assembly having part number (P/N) 251W1130–1, install yoke assembly having P/N 251W1130–3. Optional Terminating Action for Certain Repetitive Inspections (h) For Model 777–200 and –300 series airplanes identified in Boeing Service Bulletin 777–27–0049, dated August 30, 2001: Replacing the yoke assemblies of the left inboard, left outboard, right inboard, and right outboard flaperon PCUs with new, improved yoke assemblies having improved bearing retention, and doing any other specified and corrective actions, by doing all of the actions specified in the Accomplishment Instructions of Boeing Service Bulletin 777–27–0049, dated August 30, 2001, terminates the detailed inspections required by paragraphs (f)(3) and (f)(4) of this AD. Credit for Pin Replacements of the Outboard Flaperon PCUs (i) Accomplishment of the actions specified in paragraph (b) or (d) of AD 99– 13–05, amendment 39–11198, before the effective date of this AD is acceptable for compliance with the pin replacements of the left and right outboard flaperon PCUs required by paragraph (g) of this AD. Parts Installation (j) As of the effective date of this AD, no person may install on any airplane the following parts: Yoke assembly having P/N S251W115–3 or P/N 251W1130–1; and pin having P/N S251W115–2. Alternative Methods of Compliance (AMOCs) (k)(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 Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those VerDate jul<14>2003 17:25 Jun 02, 2005 Jkt 205001 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 May 27, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11049 Filed 6–2–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21355; Directorate Identifier 2005–NM–037–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767 Series Airplanes Powered by General Electric or Pratt & Whitney Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Boeing Model 767 series airplanes. The existing AD currently requires repetitive inspections to detect discrepancies of the eight aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions if necessary. That AD also provides an optional terminating action for the repetitive inspections. This proposed AD would add repetitive inspections for cracks of the closeout angle that covers the two aft-most fasteners in the lower tang of the midspar fitting, and related investigative and corrective actions if necessary. This proposed AD also would reduce the inspection interval of the upper tang of the outboard midspar fitting; and would provide an optional terminating action for the repetitive inspections. This proposed AD is prompted by a report of a crack in a closeout angle that covers the two aftmost fasteners in the lower tang of the midspar fitting; and the discovery of a PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 crack in the lower tang of the midspar fitting under the cracked closeout angle. We are proposing this AD to prevent fatigue cracking in the primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine. DATES: We must receive comments on this proposed AD by July 18, 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. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. You can examine the contents of this AD docket on the Internet at http:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 21355; the directorate identifier for this docket is 2005–NM–037–AD. FOR FURTHER INFORMATION CONTACT: Suzanne Masterson, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6441; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– E:\FR\FM\03JNP1.SGM 03JNP1 32528 Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules 2005–21355; Directorate Identifier 2005–NM–037–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 our docket 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 can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit http:// dms.dot.gov. Examining the Docket You can 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 DMS receives them. Discussion On April 22, 2004, we issued AD 2004–09–14, amendment 39–13603 (69 FR 24947, May 5, 2004), for certain Boeing Model 767 series airplanes. That AD requires repetitive inspections to detect discrepancies of the eight aftmost fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions if necessary. That AD also provides an optional terminating action for the repetitive inspections. That AD was prompted by reports of cracking at the third row of fasteners in the midspar fitting. We issued that AD to prevent fatigue cracking in the primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine. Actions Since Existing AD Was Issued Since we issued that AD, an operator doing the inspections required by AD 2004–09–14 discovered a crack in the closeout angle that covers the two aftmost fasteners in the lower tang of the midspar fitting and found that the midspar fitting, where it was hidden by the closeout angle, was also cracked. The closeout angle does not normally carry high fatigue loads, so a cracked closeout angle is a symptom of cracking in the midspar fitting at the fastener locations under the closeout angle. The existing AD requires an inspection of the closeout angle, but does not require that operators inspect the midspar fitting under the angle if the detailed inspection option (one of two options for compliance) is chosen. Analysis has shown that the detailed inspection of the closeout angle does not provide sufficient probability of detecting the secondary cracking resulting from a cracked midspar fitting. The same analysis showed that the repetitive interval for inspecting the upper tang of the outboard midspar fitting is insufficient. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 767–54A0101, Revision 4, dated February 10, 2005 (AD 2004– 09–14 refers to Boeing Service Bulletin 767–54A0101, Revision 3, dated September 5, 2002, as the appropriate source of service information for the actions specified in that AD). The alert service bulletin describes procedures for the repetitive detailed inspections or high-frequency eddy current (HFEC) inspections of the aft-most fastener holes that are mandated by the existing AD. In addition, the alert service bulletin describes procedures for repetitive HFEC inspections of the closeout angle around the two fasteners common to the closeout angle and the midspar fitting. If no crack or incorrect fastener hole diameter is found during any inspection, the alert service bulletin describes procedures for doing any necessary rework of the fastener holes, and repeating the inspection at intervals ranging from 600 flight cycles to 16,000 flight cycles, depending on the type of engine, the area to be inspected, and the inspections accomplished previously according to the existing AD. In this revision of the service bulletin, the repetitive inspection interval for the detailed inspection of the upper tangs of the outboard midspar fitting is reduced from 6,000 flight cycles to 1,500 flight cycles. If any crack is found during any inspection of the closeout angle, the service bulletin describes procedures for related investigative and corrective actions. The related actions are to remove the two fasteners common to the closeout angle and the midspar fitting, and do an HFEC inspection for discrepancies (cracks, incorrect fastener hole diameter) of the fastener holes of the closeout angle. If there are no discrepancies in the open fastener holes, the corrective action is to contact the manufacturer for repair instructions for the closeout angle. If cracks are found both in the closeout angle and the open fastener holes, or if any of the eight fastener holes are larger than 0.5322 inch, the corrective action is to do the terminating action in Part 4 of the alert service bulletin, or to contact the manufacturer for repair instructions. Accomplishing the actions specified in Boeing Alert Service Bulletin 767– 54A0101, Revision 4, is intended to adequately address the unsafe condition. The alert service bulletin refers to the Boeing service bulletins in the following table as additional sources of service information for doing the terminating action in Part 4 of the alert service bulletin. ADDITIONAL SOURCES OF SERVICE INFORMATION Boeing service bulletin Revision level Date Title 767–54–0052 ................................. Original ......................................... June 11, 1992 ............................... 767–54–0061 ................................. 2 .................................................... November 23, 1999 ...................... Nacelles/Pylons—Strut—Aft Lower Spar—Fastener Corrosion—Inspection and Replacement. Nacelles/Pylons—Wing-to-Strut Attach Fittings—Lower Spar Bushing Inspection and Replacement. VerDate jul<14>2003 17:32 Jun 02, 2005 Jkt 205001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\03JNP1.SGM 03JNP1 32529 Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules ADDITIONAL SOURCES OF SERVICE INFORMATION—Continued Boeing service bulletin Revision level Date Title 767–54–0069 ................................. 2 .................................................... August 31, 2000 ........................... 767–54–0072 ................................. Original ......................................... March 13, 1997 ............................ 767–54–0080 ................................. 1 .................................................... May 9, 2002 .................................. 767–54–0081 ................................. 1 .................................................... February 7, 2002 .......................... 767–54A0062 ................................. 5 .................................................... November 11, 2002 ...................... 767–54A0074 ................................. Original ......................................... March 27, 1997 ............................ 767–54A0094 ................................. 2 .................................................... February 7, 2002 .......................... 767–57–0063 ................................. 1 .................................................... November 30, 2000 ...................... Nacelles/Pylons—Midspar Fitting—Underwing Sideload Fitting—Fuse Pin Replacement and Wing Rework. Nacelles/Pylons—Strut Attach Upper Link—Upper Link Inspection, Rework, or Replacement. Nacelles/Pylons—Pratt and Whitney Powered Airplanes—Nacelle Strut and Wing Structure Modification. Nacelles/Pylons—General Electric Powered Airplanes—Nacelle Strut and Wing Structure Modification. Nacelles/Pylons—Strut Attach Fuse Pins—Midspar Fuse Pin Inspection and Replacement. Nacelles/Pylons—Strut Attach Fuse Pins—Upper link Fuse Pin Inspection/Replacement. Nacelles/Pylons—Strut-to-Wing Attachment—Diagonal Brace Inspection/Rework/Replacement. Wings—Side Load Underwing Fitting—Inspection/Rework. Other Relevant Rulemaking The FAA has issued the following ADs that are related to the additional sources of service information listed in the table above. • AD 94–11–02, amendment 39–8918 (59 FR 27229, May 26, 1994), applicable to all Boeing Model 767 series airplanes, and related to Boeing Alert Service Bulletin 767–54A0062. AD 94–11–02 requires repetitive detailed visual and eddy current inspections to detect cracks of certain midspar fuse pins, and replacement of any cracked midspar fuse pin with a new fuse pin. • AD 99–07–06, amendment 39– 11091 (64 FR 14578, March 26, 1999), applicable to certain Boeing Model 767 series airplanes, and related to Boeing Alert Service Bulletin 767–54A0094. AD 99–07–06 requires repetitive inspections to detect cracking or damage of the forward and aft lugs of the diagonal brace of the nacelle strut; follow-on actions, if necessary; and an optional terminating action for the repetitive inspections. AD 99–07–06 was superseded by AD 2000–07–05. • AD 2000–07–05, amendment 39– 11659 (65 FR 18883, April 10, 2000), applicable to certain Boeing Model 767 series airplanes, and related to Boeing Alert Service Bulletin 767–54A0094. AD 2000–07–05 requires the previously optional terminating action of AD 99– 07–06. • AD 2000–10–51, amendment 39– 11770 (65 FR 37011, June 13, 2000), VerDate jul<14>2003 17:25 Jun 02, 2005 Jkt 205001 applicable to certain Boeing Model 767 series airplanes, and related to Boeing Service Bulletin 767–54A0074. AD 2000–10–51 requires a one-time inspection to determine whether certain bolts are installed in the side load underwing fittings on both struts, and various follow-on actions, if necessary. • AD 2001–02–07, amendment 39– 12091 (66 FR 8085, January 29, 2001), applicable to certain Boeing Model 767 series airplanes powered by Pratt & Whitney engines, and related to Boeing Service Bulletins 767–54–0069 and 767–54–0080; and Boeing Alert Service Bulletin 767–54A0094. AD 2001–02–07 requires modification of the nacelle strut and wing structure. This AD terminates certain requirements of AD 94–11–02. • AD 2001–06–12, amendment 39– 12159 (66 FR 17492, April 2, 2001), applicable to certain Boeing Model 767 series airplanes powered by General Electric engines, and related to Boeing Service Bulletins 767–54–0069 and 767–54–0081; and Boeing Alert Service Bulletin 767–54A0094. AD 2001–06–12 requires modification of the nacelle strut and wing structure. This AD terminates certain requirements of AD 94–11–02. • AD 2003–03–02, amendment 39– 13026 (68 FR 4374, January 29, 3003), applicable to all Boeing Model 767 series airplanes, and related to Boeing Service Bulletin 767–54A0062. AD 2003–03–02 supersedes AD 94–11–02. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 AD 2003–03–02 retains the requirements of AD 94–11–02, but reduces certain compliance times for certain inspections, expands the detailed and eddy current inspections, and limits the applicability. FAA’s Determination and Requirements of the Proposed AD The unsafe condition described previously is likely to exist or develop on other airplanes of the same type design that may be registered in the U.S. at some time in the future. We are proposing to supersede AD 2004–09–14. This proposed AD would continue to require repetitive inspections to detect discrepancies of the eight aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions if necessary; and continue to provide an optional terminating action for the repetitive inspections. This proposed AD also would require repetitive inspections for cracks of the closeout angle that covers the two aft-most fasteners in the lower tang of the midspar fitting, and related investigative and corrective actions if necessary; and would reduce the inspection interval of the upper tang of the outboard midspar fitting; except as discussed under ‘‘Difference Between the Proposed AD and the Alert Service Bulletin,’’ and ‘‘Differences Between the Proposed AD and Boeing Service Bulletin 767–54–0074 (an Additional Source of Service Information).’’ E:\FR\FM\03JNP1.SGM 03JNP1 32530 Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules Difference Between the Proposed AD and the Alert Service Bulletin The service bulletin specifies that you may contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require you to repair 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 Delegation Option Authorization Organization whom we have authorized to make those findings. Differences Between the Proposed AD and Boeing Service Bulletin 767–54– 0074 (an Additional Source of Service Information) Boeing Service Bulletin 767–54–0074, dated March 27, 1997, contains erroneous technical information that was later corrected by the following information notices (INs): • IN 767–54–0074 IN 01, dated October 29, 1998, informs operators that Step E.2.b of the Accomplishment Instructions of Boeing Service Bulletin 767–54–0074 should read ‘‘If no crack indication is found, continue to Step F.’’ instead of ‘‘If no crack indication is found, reinstall the fuse pin.’’ • IN 767–54–0074 IN 02, dated June 14, 2001, informs operators that the part number of the cotter pin referenced in the material information section should be MS24665–374 rather than MS25665– 374. Table 4 of this proposed AD incorporates these corrections. Changes to Existing AD Since AD 2004–09–14 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Corresponding requirement in this proposed AD Requirement in AD 2004–09–14 Paragraph Paragraph Paragraph Paragraph Paragraph (a) (b) (c) (d) (e) ...................... ...................... ...................... ...................... ...................... Paragraph Paragraph Paragraph Paragraph Paragraph (f). (g). (h). (i). (j). REVISED PARAGRAPH IDENTIFIERS— Continued Corresponding requirement in this proposed AD Requirement in AD 2004–09–14 Paragraph Paragraph Paragraph Paragraph Paragraph (f) ....................... (g) ...................... (h) ...................... (i) ....................... (j) ....................... Paragraph Paragraph Paragraph Paragraph Paragraph (k). (l). (m). (n). (o). This proposed AD would retain all requirements of AD 2004–09–14. However, we have revised the provisions of paragraph (d) of AD 2004– 09–14 (which is included as paragraph (i) of this proposed AD) to include wording related to the new actions in paragraph (p) of this proposed AD. We have revised the applicability to identify model designations as published in the most recent type certificate data sheet for the affected models. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Action Average labor rate per hour Work hours Option 1: Detailed inspection (required by AD 2004–09– 14). Option 2: HFEC inspection (required by AD 2004–09– 14). HFEC inspection (new proposed action). Number of U.S.-registered airplanes Fleet cost $65 None ........... $65, per inspection cycle. 263 N/A (depends on chosen option). 3 65 None ........... 195, per inspection cycle. 263 N/A (depends on chosen option). 4 65 None ........... 260, per inspection cycle. 263 $68,380, per inspection cycle. 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 17:25 Jun 02, 2005 Cost per airplane 1 Authority for This Rulemaking VerDate jul<14>2003 Parts Jkt 205001 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 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 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. 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: E:\FR\FM\03JNP1.SGM 03JNP1 Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules 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 FAA amends § 39.13 by removing amendment 39–13603 (69 FR 24947, May 5, 2004) and adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2005–21355; Directorate Identifier 2005–NM–037–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by July 18, 2005. Affected ADs (b) This AD supersedes AD 2004–09–14, amendment 39–13603 (69 FR 24947, May 5, 2004). Applicability (c) This AD applies to Boeing Model 767– 200, –300, –300F, and –400ER series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 767–54A0101, Revision 4, dated February 10, 2005. Unsafe Condition (d) This AD was prompted by a report of a crack in a closeout angle that covers the two aft-most fasteners in the lower tang of the midspar fitting; and the discovery of a crack in the lower tang of the midspar fitting under the cracked closeout angle. We are issuing this AD to prevent fatigue cracking in the primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine. 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. Restatement of Requirements of AD 2004– 09–14 Repetitive Inspections (f) Except as provided by paragraph (g) of this AD, before the accumulation of 10,000 total flight cycles, or within 600 flight cycles after May 15, 2001 (the effective date of AD 2001–07–05, amendment 39–12170), whichever occurs later: Accomplish the inspections required by paragraph (f)(1) or (f)(2) of this AD, as applicable. (1) Perform a detailed inspection of the four aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut to detect cracking, in accordance with Part 1, ‘‘Detailed Inspection,’’ of the Accomplishment Instructions of Boeing Service Bulletin 767–54A0101, Revision 1, dated February 3, 2000. If no cracking is VerDate jul<14>2003 17:25 Jun 02, 2005 Jkt 205001 detected, repeat the inspection thereafter at the applicable intervals specified in Table 1, ‘‘Reinspection Intervals for Part 1—Detailed Inspection’’ included in Figure 1 of the service bulletin. 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.’’ (2) Perform a high frequency eddy current (HFEC) inspection of the four aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut to detect discrepancies (cracking, incorrect fastener hole diameter), in accordance with Part 2, ‘‘High Frequency Eddy Current (HFEC) Inspection,’’ of the Accomplishment Instructions of the service bulletin. Accomplish the requirements specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, as applicable; and repeat the inspection thereafter at the applicable intervals specified in Table 2, ‘‘Reinspection Intervals for Part 2—HFEC Inspection’’ included in Figure 1 of the service bulletin. (i) If no cracking is detected and the fastener hole diameter is less than or equal to 0.5322 inch, before further flight, rework the hole in accordance with Part 3 of the Accomplishment Instructions of the service bulletin. (ii) If no cracking is detected and the fastener hole diameter is greater than 0.5322 inch, before further flight, accomplish the requirements specified in either paragraph (h)(1) or (h)(2) of this AD. (g) For airplanes on which the two aft-most fasteners have been inspected in accordance with Boeing Service Bulletin 767–54A0101, Revision 1, dated February 3, 2000, prior to May 15, 2001: Perform the initial inspection of the four aft-most fasteners in accordance with paragraph (f) of this AD before the accumulation of 10,000 total flight cycles, or within 1,500 flight cycles after May 15, 2001, whichever occurs later. Corrective Actions (h) If any cracking is detected after accomplishment of any inspection required by paragraph (f) of this AD, before further flight, accomplish the requirements specified in either paragraph (h)(1) or (h)(2) of this AD. (1) Accomplish the terminating action specified in Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 767– 54A0101, Revision 1, dated February 3, 2000; Boeing Service Bulletin 767–54A0101, Revision 3, dated September 5, 2002; or Boeing Alert Service Bulletin 767–54A0101, Revision 4, dated February 10, 2005. Accomplishment of this paragraph terminates the requirements of this AD. After the effective date of this AD, only Boeing Alert Service Bulletin 767–54A0101, Revision 4, may be used. PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 32531 (2) Replace the midspar fitting of the strut with a serviceable part, or repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Repeat the applicable inspection thereafter at the applicable time specified in paragraph (f)(1) or (f)(2) of this AD. (i) If any discrepancies (cracking, incorrect fastener hole diameter) are detected during any inspection required by paragraph (f) or (p) of this AD, for which the service bulletin specifies that the manufacturer may be contacted for disposition of those repair conditions: Before further flight, accomplish the applicable related investigative and corrective actions (including fastener hole rework and/or midspar fitting replacement) according to a method approved by the Manager, Seattle ACO; or in accordance with data meeting the certification basis of the airplane approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make such findings. For a method to be approved, the approval must specifically reference this AD. Additional Inspections (j) Prior to the accumulation of 10,000 total flight cycles, or within 600 flight cycles after June 9, 2004 (the effective date of AD 2004– 09–14), whichever occurs later: Perform the inspections specified in paragraph (f)(1) or (f)(2) of this AD, as applicable, on all eight aft-most fastener holes or the four forward fastener holes in the group of eight aft-most fastener holes not inspected per paragraph (f)(1), (f)(2), or (g) of this AD. The inspection must be done per the Accomplishment Instructions in Boeing Service Bulletin 767– 54A0101, Revision 3, dated September 5, 2002; or Boeing Alert Service Bulletin 767– 54A0101, Revision 4, dated February 10, 2005. Accomplishment of the applicable inspection on all eight aft-most fastener holes constitutes terminating action for the repetitive inspection requirements of paragraphs (f)(1), (f)(2), and (g) of this AD. (k) If no cracking or discrepancy is detected during any detailed inspection required by paragraph (j) of this AD, repeat the inspections of all eight aft-most fastener holes thereafter at the applicable intervals specified in Table 1 of this AD. (l) If no cracking or discrepancy is detected during any HFEC inspection required by paragraph (j) of this AD or by this paragraph of this AD: Perform the follow-on actions specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, as applicable, per the Accomplishment Instructions in Boeing Service Bulletin 767–54A0101, Revision 3, dated September 5, 2002; or Boeing Alert Service Bulletin 767–54A0101, Revision 4, dated February 10, 2005; and repeat the inspections of all eight aft-most fastener holes thereafter at the applicable intervals specified in Table 1 of this AD. E:\FR\FM\03JNP1.SGM 03JNP1 32532 Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules TABLE 1.—REPETITIVE INSPECTION INTERVALS FOR ALL EIGHT AFT-MOST FASTENER HOLES If— Repetitive intervals— (1) All eight aft-most fastener holes were inspected per paragraph (j) of this AD: At the applicable intervals specified in Table 1, ‘‘Reinspection Intervals for Part 1,’’ or Table 2, ‘‘Reinspection Intervals for Part 2,’’ as applicable. Both tables are included in Figure 1 of the applicable service bulletin. Within 1,500 flight cycles after the effective date of this AD, only the repetitive intervals in Boeing Alert Service Bulletin 767–54A0101, Revision 4, dated February 10, 2005, may be used. At the next scheduled repetitive inspection required by paragraph (f)(1) or (f)(2) of this AD, as applicable. Thereafter at the applicable intervals specified in Table 1, ‘‘Reinspection Intervals for Part 1,’’ or Table 2, ‘‘Reinspection Intervals for Part 2,’’ as applicable. Both tables are included in Figure 1 of the applicable service bulletin. Within 1,500 flight cycles after the effective date of this AD, only the repetitive intervals in Boeing Alert Service Bulletin 767–54A0101, Revision 4, dated February 10, 2005, may be used. (2) Only the four forward fastener holes in the group of eight aft-most fastener holes were inspected per paragraph (j) of this AD: Corrective Actions for Discrepancies (m) If any cracking or discrepancy is detected during any inspection required by paragraphs (j), (k), or (l) of this AD, before further flight: Accomplish the corrective actions described in paragraph (h) of this AD, except as provided in paragraph (i) of this AD. Service Bulletin Revisions (n) Accomplishing the terminating action in paragraph (h)(1) of this AD before June 9, 2004 (the effective date of AD 2004–09–14) in accordance with the service bulletin revisions in Table 2 of this AD, is acceptable for compliance with the requirements of this AD. After the effective date of this AD, only Boeing Alert Service Bulletin 767–54A0101, Revision 4, dated February 10, 2005, may be used for accomplishing the terminating action in paragraph (h)(1) of this AD. TABLE 2.—SERVICE BULLETIN REVISIONS FOR TERMINATING ACTION Boeing service bulletin Revision Date 767–54A0101 ...................................................................................................................................... 767–54A0101 ...................................................................................................................................... Original .................... 2 ............................... September 23, 1999. January 10, 2002. Inspections Accomplished per Previous Issues of Service Bulletin (o) Inspections required by paragraphs (f) and (g) of this AD that are accomplished before June 9, 2004 in accordance with the service bulletin revisions in Table 3 of this AD are considered acceptable for compliance with the corresponding action specified in this AD. TABLE 3.—SERVICE BULLETIN REVISIONS FOR PREVIOUSLY ACCOMPLISHED INSPECTIONS Boeing service bulletin Revision 767–54A0101 ........................................................................................................................................................ 767–54A0101 ........................................................................................................................................................ 767–54A0101 ........................................................................................................................................................ New Requirements of This AD Inspections of Closeout Angle and Corrective Action (p) For airplanes for which the ‘‘Reinspection Intervals for Part 1,’’ referenced in Table 1 of paragraph (l) of this AD apply: At the next applicable inspection, do an HFEC inspection for cracks of the closeout angle that covers the two aft-most fasteners in the lower tang of the midspar fitting and any related investigative and corrective actions, by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 767–54A0101, Revision 4, dated February 10, 2005. Repeat the inspection at the applicable interval in Table 1, ‘‘Reinspection Intervals 2 3 4 Date January 10, 2002. September 5, 2002. February 10, 2005. for Part 1,’’ in Figure 1 of the alert service bulletin. Note 2: Boeing Alert Service Bulletin 767– 54A0101, Revision 4, dated February 10, 2005, refers to the Boeing service bulletins in the Table 4 of this AD as additional sources of service information for doing the terminating action in paragraph (h)(1) of this AD. TABLE 4.—ADDITIONAL SOURCES OF SERVICE INFORMATION Boeing service bulletin Revision level Date Title 767–54–0052 ................................. Original ......................................... June 11, 1992 ............................... Nacelles/Pylons—Strut—Aft Lower Spar—Fastener Corrosion—Inspection and Replacement. VerDate jul<14>2003 17:25 Jun 02, 2005 Jkt 205001 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 E:\FR\FM\03JNP1.SGM 03JNP1 32533 Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules TABLE 4.—ADDITIONAL SOURCES OF SERVICE INFORMATION—Continued Boeing service bulletin Revision level Date Title 767–54–0061 ................................. 2 .................................................... November 23, 1999 ...................... 767–54–0069 ................................. 2 .................................................... August 31, 2000 ........................... 767–54–0072 ................................. Original ......................................... March 13, 1997 ............................ 767–54–0074 ................................. Original ......................................... March 27, 1997 ............................ 767–54–0080 ................................. 1 .................................................... May 9, 2002 .................................. 767–54–0081 ................................. 1 .................................................... February 7, 2002 .......................... 767–54A0062 ................................. 5 .................................................... November 11, 2002 ...................... 767–54A0094 ................................. 2 .................................................... February 7, 2002 .......................... 767–57–0063 ................................. 1 .................................................... November 30, 2000 ...................... Nacelles/Pylons—Wing-to-Strut Attach Fittings—Lower Spar Bushing Inspection and Replacement. Nacelles/Pylons—Midspar Fitting—Underwing Sideload Fitting—Fuse Pin Replacement and Wing Rework. Nacelles/Pylons—Strut Attach Upper Link—Upper Link Inspection, Rework, or Replacement. Nacelles/Pylons—Strut Attach Fuse Pins—Upper link Fuse Pin Inspection/Replacement. Where this service bulletin refers to a cotter pin with part number (P/ N) MS 25665–374, the P/N should be MS24665–374. Where this service bulletin says, ‘‘If no crack indication is found, reinstall the fuse pin,’’ the correct statement is ‘‘If no crack indication is found, continue to Step F.’’ Nacelles/Pylons—Pratt and Whitney Powered Airplanes—Nacelle Strut and Wing Structure Modification. Nacelles/Pylons—General Electric Powered Airplanes—Nacelle Strut and Wing Structure Modification. Nacelles/Pylons—Strut Attach Fuse Pins—Midspar Fuse Pin Inspection and Replacement. Nacelles/Pylons—Strut-to-Wing Attachment—Diagonal Brace Inspection/Rework/Replacement. Wings—Side Load Underwing Fitting—Inspection/Rework. Note 3: Certain service bulletins referenced in Table 4 of this AD are related to the ADs listed in Table 5 of this AD. TABLE 5.—OTHER RELEVANT RULEMAKING AD Applicability Related Boeing service bulletin AD requirement AD 94–11–02, amendment 39– 8919, (59 FR 27229, June 10, 1994). All Boeing Model 767 series airplanes. 767–54A0062 ............................... AD 99–07–06, amendment 39– 11091 (64 FR 14578, March 26, 1999). Certain Boeing Model 767 series airplanes. 767–54A0094 ............................... AD 2000–07–05, amendment 39– 11659 (65 FR 18883, April 10, 2000). Certain Boeing Model 767 series airplanes. 767–54A0094 ............................... Repetitive detailed visual and eddy current inspections to detect cracks of certain midspar fuse pins, and replacement of any cracked midspar fuse pin with a new fuse pin. Repetitive inspections to detect cracking or damage of the forward and aft lugs of the diagonal brace of the nacelle strut; follow-on actions, if necessary; and an optional terminating action for the repetitive inspections. Superseded by AD 2000– 07–05. Requires the previously optional terminating action of AD 99– 07–06. VerDate jul<14>2003 17:25 Jun 02, 2005 Jkt 205001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\03JNP1.SGM 03JNP1 32534 Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules TABLE 5.—OTHER RELEVANT RULEMAKING—Continued AD Applicability Related Boeing service bulletin AD requirement AD 2000–10–15, amendment 39– 11770 (65 FR 37011, June 13, 2000). Certain Boeing Model 767 series airplanes. 767–54–0074 ................................ AD 2001–02–07, amendment 39– 12091 (66 FR 8085, January 29, 2001). Certain Boeing Model 767 series airplanes powered by Pratt & Whitney engines. 767–54–0069, 767–54–0080, and 767–54A0094. AD 2001–06–12, amendment 39– 12159 (66 FR 17492, April 2, 2001). Certain Boeing Model 767 series airplanes powered by General Electric engines. 767–54–0069, 767–54–0081, and 767–54A0094. AD 2003–03–02, amendment 39– 13026 (68 FR 4374, January 29, 2003). All Boeing Model 767 series airplanes. 767–54A0062 ............................... One-time inspection to determine whether certain bolts are installed in the side load underwing fittings on both struts, and various follow-on actions, if necessary. Modification of the nacelle strut and wing structure. Terminates certain requirements of AD 94– 11–02. Modification of the nacelle strut and wing structure. Terminates certain requirements of AD 94– 11–02. Supersedes AD 94–11–02; Retains all requirements but reduces certain compliance times for certain inspections, expands the detailed and eddy current inspections,and limits the applicability. Alternative Methods of Compliance (AMOCs) (q)(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) AMOCS approved previously according to AD 2004–09–14, amendment 39–13603, are approved as AMOCs for the corresponding requirements of this AD. (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 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 May 26, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11050 Filed 6–2–05; 8:45 am] BILLING CODE 4910–13–P VerDate jul<14>2003 17:25 Jun 02, 2005 Jkt 205001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21346; Directorate Identifier 2005–NM–031–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–100, –200, –200C, –300, –400, and –500 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This proposed AD would require operators to examine the airplane’s maintenance records to determine if the main landing gear (MLG) has been overhauled and if Titanine JC5A (also known as Desoto 823E508) corrosioninhibiting compound (‘‘C.I.C.’’) was used during the overhaul. For airplanes for which the maintenance records indicate that further action is necessary, or for airplanes on which C.I.C. JC5A may have been used during manufacture, this proposed AD would require a one-time detailed inspection for discrepancies of certain components of the MLG, and corrective action if necessary. This proposed AD is prompted by twelve reports of severe corrosion on one or more of three PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 components of the MLG. We are proposing this AD to prevent collapse of the MLG, or damage to hydraulic tubing or the aileron control cables, which could result in possible departure of the airplane from the runway and loss of control of the airplane. DATES: We must receive comments on this proposed AD by July 18, 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. • By 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. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. You can examine the contents of this AD docket on the Internet at http:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– E:\FR\FM\03JNP1.SGM 03JNP1

Agencies

[Federal Register Volume 70, Number 106 (Friday, June 3, 2005)]
[Proposed Rules]
[Pages 32527-32534]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-11050]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21355; Directorate Identifier 2005-NM-037-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767 Series Airplanes 
Powered by General Electric or Pratt & Whitney Engines

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Boeing Model 767 series 
airplanes. The existing AD currently requires repetitive inspections to 
detect discrepancies of the eight aft-most fastener holes in the 
horizontal tangs of the midspar fitting of the strut, and corrective 
actions if necessary. That AD also provides an optional terminating 
action for the repetitive inspections. This proposed AD would add 
repetitive inspections for cracks of the closeout angle that covers the 
two aft-most fasteners in the lower tang of the midspar fitting, and 
related investigative and corrective actions if necessary. This 
proposed AD also would reduce the inspection interval of the upper tang 
of the outboard midspar fitting; and would provide an optional 
terminating action for the repetitive inspections. This proposed AD is 
prompted by a report of a crack in a closeout angle that covers the two 
aft-most fasteners in the lower tang of the midspar fitting; and the 
discovery of a crack in the lower tang of the midspar fitting under the 
cracked closeout angle. We are proposing this AD to prevent fatigue 
cracking in the primary strut structure and reduced structural 
integrity of the strut, which could result in separation of the strut 
and engine.

DATES: We must receive comments on this proposed AD by July 18, 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.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street, SW., room PL-
401, on the plaza level of the Nassif Building, Washington, DC. This 
docket number is FAA-2005-21355; the directorate identifier for this 
docket is 2005-NM-037-AD.

FOR FURTHER INFORMATION CONTACT: Suzanne Masterson, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6441; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-

[[Page 32528]]

2005-21355; Directorate Identifier 2005-NM-037-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 our 
docket 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 can review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.

Examining the Docket

    You can 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 DMS receives them.

Discussion

    On April 22, 2004, we issued AD 2004-09-14, amendment 39-13603 (69 
FR 24947, May 5, 2004), for certain Boeing Model 767 series airplanes. 
That AD requires repetitive inspections to detect discrepancies of the 
eight aft-most fastener holes in the horizontal tangs of the midspar 
fitting of the strut, and corrective actions if necessary. That AD also 
provides an optional terminating action for the repetitive inspections. 
That AD was prompted by reports of cracking at the third row of 
fasteners in the midspar fitting. We issued that AD to prevent fatigue 
cracking in the primary strut structure and reduced structural 
integrity of the strut, which could result in separation of the strut 
and engine.

Actions Since Existing AD Was Issued

    Since we issued that AD, an operator doing the inspections required 
by AD 2004-09-14 discovered a crack in the closeout angle that covers 
the two aft-most fasteners in the lower tang of the midspar fitting and 
found that the midspar fitting, where it was hidden by the closeout 
angle, was also cracked. The closeout angle does not normally carry 
high fatigue loads, so a cracked closeout angle is a symptom of 
cracking in the midspar fitting at the fastener locations under the 
closeout angle. The existing AD requires an inspection of the closeout 
angle, but does not require that operators inspect the midspar fitting 
under the angle if the detailed inspection option (one of two options 
for compliance) is chosen. Analysis has shown that the detailed 
inspection of the closeout angle does not provide sufficient 
probability of detecting the secondary cracking resulting from a 
cracked midspar fitting. The same analysis showed that the repetitive 
interval for inspecting the upper tang of the outboard midspar fitting 
is insufficient.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 767-54A0101, 
Revision 4, dated February 10, 2005 (AD 2004-09-14 refers to Boeing 
Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002, as 
the appropriate source of service information for the actions specified 
in that AD). The alert service bulletin describes procedures for the 
repetitive detailed inspections or high-frequency eddy current (HFEC) 
inspections of the aft-most fastener holes that are mandated by the 
existing AD. In addition, the alert service bulletin describes 
procedures for repetitive HFEC inspections of the closeout angle around 
the two fasteners common to the closeout angle and the midspar fitting.
    If no crack or incorrect fastener hole diameter is found during any 
inspection, the alert service bulletin describes procedures for doing 
any necessary rework of the fastener holes, and repeating the 
inspection at intervals ranging from 600 flight cycles to 16,000 flight 
cycles, depending on the type of engine, the area to be inspected, and 
the inspections accomplished previously according to the existing AD. 
In this revision of the service bulletin, the repetitive inspection 
interval for the detailed inspection of the upper tangs of the outboard 
midspar fitting is reduced from 6,000 flight cycles to 1,500 flight 
cycles.
    If any crack is found during any inspection of the closeout angle, 
the service bulletin describes procedures for related investigative and 
corrective actions. The related actions are to remove the two fasteners 
common to the closeout angle and the midspar fitting, and do an HFEC 
inspection for discrepancies (cracks, incorrect fastener hole diameter) 
of the fastener holes of the closeout angle. If there are no 
discrepancies in the open fastener holes, the corrective action is to 
contact the manufacturer for repair instructions for the closeout 
angle. If cracks are found both in the closeout angle and the open 
fastener holes, or if any of the eight fastener holes are larger than 
0.5322 inch, the corrective action is to do the terminating action in 
Part 4 of the alert service bulletin, or to contact the manufacturer 
for repair instructions.
    Accomplishing the actions specified in Boeing Alert Service 
Bulletin 767-54A0101, Revision 4, is intended to adequately address the 
unsafe condition.
    The alert service bulletin refers to the Boeing service bulletins 
in the following table as additional sources of service information for 
doing the terminating action in Part 4 of the alert service bulletin.

                                    Additional Sources of Service Information
----------------------------------------------------------------------------------------------------------------
       Boeing service bulletin              Revision level                Date                    Title
----------------------------------------------------------------------------------------------------------------
767-54-0052..........................  Original...............  June 11, 1992..........  Nacelles/Pylons--Strut--
                                                                                          Aft Lower Spar--
                                                                                          Fastener Corrosion--
                                                                                          Inspection and
                                                                                          Replacement.
767-54-0061..........................  2......................  November 23, 1999......  Nacelles/Pylons--Wing-
                                                                                          to-Strut Attach
                                                                                          Fittings--Lower Spar
                                                                                          Bushing Inspection and
                                                                                          Replacement.

[[Page 32529]]

 
767-54-0069..........................  2......................  August 31, 2000........  Nacelles/Pylons--
                                                                                          Midspar Fitting--
                                                                                          Underwing Sideload
                                                                                          Fitting--Fuse Pin
                                                                                          Replacement and Wing
                                                                                          Rework.
767-54-0072..........................  Original...............  March 13, 1997.........  Nacelles/Pylons--Strut
                                                                                          Attach Upper Link--
                                                                                          Upper Link Inspection,
                                                                                          Rework, or
                                                                                          Replacement.
767-54-0080..........................  1......................  May 9, 2002............  Nacelles/Pylons--Pratt
                                                                                          and Whitney Powered
                                                                                          Airplanes--Nacelle
                                                                                          Strut and Wing
                                                                                          Structure
                                                                                          Modification.
767-54-0081..........................  1......................  February 7, 2002.......  Nacelles/Pylons--
                                                                                          General Electric
                                                                                          Powered Airplanes--
                                                                                          Nacelle Strut and Wing
                                                                                          Structure
                                                                                          Modification.
767-54A0062..........................  5......................  November 11, 2002......  Nacelles/Pylons--Strut
                                                                                          Attach Fuse Pins--
                                                                                          Midspar Fuse Pin
                                                                                          Inspection and
                                                                                          Replacement.
767-54A0074..........................  Original...............  March 27, 1997.........  Nacelles/Pylons--Strut
                                                                                          Attach Fuse Pins--
                                                                                          Upper link Fuse Pin
                                                                                          Inspection/
                                                                                          Replacement.
767-54A0094..........................  2......................  February 7, 2002.......  Nacelles/Pylons--Strut-
                                                                                          to-Wing Attachment--
                                                                                          Diagonal Brace
                                                                                          Inspection/Rework/
                                                                                          Replacement.
767-57-0063..........................  1......................  November 30, 2000......  Wings--Side Load
                                                                                          Underwing Fitting--
                                                                                          Inspection/Rework.
----------------------------------------------------------------------------------------------------------------

Other Relevant Rulemaking

    The FAA has issued the following ADs that are related to the 
additional sources of service information listed in the table above.
     AD 94-11-02, amendment 39-8918 (59 FR 27229, May 26, 
1994), applicable to all Boeing Model 767 series airplanes, and related 
to Boeing Alert Service Bulletin 767-54A0062. AD 94-11-02 requires 
repetitive detailed visual and eddy current inspections to detect 
cracks of certain midspar fuse pins, and replacement of any cracked 
midspar fuse pin with a new fuse pin.
     AD 99-07-06, amendment 39-11091 (64 FR 14578, March 26, 
1999), applicable to certain Boeing Model 767 series airplanes, and 
related to Boeing Alert Service Bulletin 767-54A0094. AD 99-07-06 
requires repetitive inspections to detect cracking or damage of the 
forward and aft lugs of the diagonal brace of the nacelle strut; 
follow-on actions, if necessary; and an optional terminating action for 
the repetitive inspections. AD 99-07-06 was superseded by AD 2000-07-
05.
     AD 2000-07-05, amendment 39-11659 (65 FR 18883, April 10, 
2000), applicable to certain Boeing Model 767 series airplanes, and 
related to Boeing Alert Service Bulletin 767-54A0094. AD 2000-07-05 
requires the previously optional terminating action of AD 99-07-06.
     AD 2000-10-51, amendment 39-11770 (65 FR 37011, June 13, 
2000), applicable to certain Boeing Model 767 series airplanes, and 
related to Boeing Service Bulletin 767-54A0074. AD 2000-10-51 requires 
a one-time inspection to determine whether certain bolts are installed 
in the side load underwing fittings on both struts, and various follow-
on actions, if necessary.
     AD 2001-02-07, amendment 39-12091 (66 FR 8085, January 29, 
2001), applicable to certain Boeing Model 767 series airplanes powered 
by Pratt & Whitney engines, and related to Boeing Service Bulletins 
767-54-0069 and 767-54-0080; and Boeing Alert Service Bulletin 767-
54A0094. AD 2001-02-07 requires modification of the nacelle strut and 
wing structure. This AD terminates certain requirements of AD 94-11-02.
     AD 2001-06-12, amendment 39-12159 (66 FR 17492, April 2, 
2001), applicable to certain Boeing Model 767 series airplanes powered 
by General Electric engines, and related to Boeing Service Bulletins 
767-54-0069 and 767-54-0081; and Boeing Alert Service Bulletin 767-
54A0094. AD 2001-06-12 requires modification of the nacelle strut and 
wing structure. This AD terminates certain requirements of AD 94-11-02.
     AD 2003-03-02, amendment 39-13026 (68 FR 4374, January 29, 
3003), applicable to all Boeing Model 767 series airplanes, and related 
to Boeing Service Bulletin 767-54A0062. AD 2003-03-02 supersedes AD 94-
11-02. AD 2003-03-02 retains the requirements of AD 94-11-02, but 
reduces certain compliance times for certain inspections, expands the 
detailed and eddy current inspections, and limits the applicability.

FAA's Determination and Requirements of the Proposed AD

    The unsafe condition described previously is likely to exist or 
develop on other airplanes of the same type design that may be 
registered in the U.S. at some time in the future. We are proposing to 
supersede AD 2004-09-14. This proposed AD would continue to require 
repetitive inspections to detect discrepancies of the eight aft-most 
fastener holes in the horizontal tangs of the midspar fitting of the 
strut, and corrective actions if necessary; and continue to provide an 
optional terminating action for the repetitive inspections. This 
proposed AD also would require repetitive inspections for cracks of the 
closeout angle that covers the two aft-most fasteners in the lower tang 
of the midspar fitting, and related investigative and corrective 
actions if necessary; and would reduce the inspection interval of the 
upper tang of the outboard midspar fitting; except as discussed under 
``Difference Between the Proposed AD and the Alert Service Bulletin,'' 
and ``Differences Between the Proposed AD and Boeing Service Bulletin 
767-54-0074 (an Additional Source of Service Information).''

[[Page 32530]]

Difference Between the Proposed AD and the Alert Service Bulletin

    The service bulletin specifies that you may contact the 
manufacturer for instructions on how to repair certain conditions, but 
this proposed AD would require you to repair 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 Delegation Option Authorization Organization whom we 
have authorized to make those findings.

Differences Between the Proposed AD and Boeing Service Bulletin 767-54-
0074 (an Additional Source of Service Information)

    Boeing Service Bulletin 767-54-0074, dated March 27, 1997, contains 
erroneous technical information that was later corrected by the 
following information notices (INs):
     IN 767-54-0074 IN 01, dated October 29, 1998, informs 
operators that Step E.2.b of the Accomplishment Instructions of Boeing 
Service Bulletin 767-54-0074 should read ``If no crack indication is 
found, continue to Step F.'' instead of ``If no crack indication is 
found, reinstall the fuse pin.''
     IN 767-54-0074 IN 02, dated June 14, 2001, informs 
operators that the part number of the cotter pin referenced in the 
material information section should be MS24665-374 rather than MS25665-
374.
    Table 4 of this proposed AD incorporates these corrections.

Changes to Existing AD

    Since AD 2004-09-14 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                           Corresponding requirement in
      Requirement in AD  2004-09-14              this proposed AD
------------------------------------------------------------------------
Paragraph (a)...........................  Paragraph (f).
Paragraph (b)...........................  Paragraph (g).
Paragraph (c)...........................  Paragraph (h).
Paragraph (d)...........................  Paragraph (i).
Paragraph (e)...........................  Paragraph (j).
Paragraph (f)...........................  Paragraph (k).
Paragraph (g)...........................  Paragraph (l).
Paragraph (h)...........................  Paragraph (m).
Paragraph (i)...........................  Paragraph (n).
Paragraph (j)...........................  Paragraph (o).
------------------------------------------------------------------------

    This proposed AD would retain all requirements of AD 2004-09-14. 
However, we have revised the provisions of paragraph (d) of AD 2004-09-
14 (which is included as paragraph (i) of this proposed AD) to include 
wording related to the new actions in paragraph (p) of this proposed 
AD.
    We have revised the applicability to identify model designations as 
published in the most recent type certificate data sheet for the 
affected models.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                             Average
                                    Work      labor                                           Number of U.S.-
             Action                hours     rate per         Parts        Cost per airplane    registered                    Fleet cost
                                               hour                                              airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Option 1: Detailed inspection            1        $65  None..............  $65, per                      263  N/A (depends on chosen option).
 (required by AD 2004-09-14).                                               inspection cycle.
Option 2: HFEC inspection                3         65  None..............  195, per                      263  N/A (depends on chosen option).
 (required by AD 2004-09-14).                                               inspection cycle.
HFEC inspection (new proposed            4         65  None..............  260, per                      263  $68,380, per inspection cycle.
 action).                                                                   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. 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:

[[Page 32531]]

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing amendment 39-13603 (69 FR 
24947, May 5, 2004) and adding the following new airworthiness 
directive (AD):

Boeing: Docket No. FAA-2005-21355; Directorate Identifier 2005-NM-
037-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by July 18, 2005.

Affected ADs

    (b) This AD supersedes AD 2004-09-14, amendment 39-13603 (69 FR 
24947, May 5, 2004).

Applicability

    (c) This AD applies to Boeing Model 767-200, -300, -300F, and -
400ER series airplanes, certificated in any category, as identified 
in Boeing Alert Service Bulletin 767-54A0101, Revision 4, dated 
February 10, 2005.

Unsafe Condition

    (d) This AD was prompted by a report of a crack in a closeout 
angle that covers the two aft-most fasteners in the lower tang of 
the midspar fitting; and the discovery of a crack in the lower tang 
of the midspar fitting under the cracked closeout angle. We are 
issuing this AD to prevent fatigue cracking in the primary strut 
structure and reduced structural integrity of the strut, which could 
result in separation of the strut and engine.

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.

Restatement of Requirements of AD 2004-09-14

Repetitive Inspections

    (f) Except as provided by paragraph (g) of this AD, before the 
accumulation of 10,000 total flight cycles, or within 600 flight 
cycles after May 15, 2001 (the effective date of AD 2001-07-05, 
amendment 39-12170), whichever occurs later: Accomplish the 
inspections required by paragraph (f)(1) or (f)(2) of this AD, as 
applicable.
    (1) Perform a detailed inspection of the four aft-most fastener 
holes in the horizontal tangs of the midspar fitting of the strut to 
detect cracking, in accordance with Part 1, ``Detailed Inspection,'' 
of the Accomplishment Instructions of Boeing Service Bulletin 767-
54A0101, Revision 1, dated February 3, 2000. If no cracking is 
detected, repeat the inspection thereafter at the applicable 
intervals specified in Table 1, ``Reinspection Intervals for Part 
1--Detailed Inspection'' included in Figure 1 of the service 
bulletin.

    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.''


    (2) Perform a high frequency eddy current (HFEC) inspection of 
the four aft-most fastener holes in the horizontal tangs of the 
midspar fitting of the strut to detect discrepancies (cracking, 
incorrect fastener hole diameter), in accordance with Part 2, ``High 
Frequency Eddy Current (HFEC) Inspection,'' of the Accomplishment 
Instructions of the service bulletin. Accomplish the requirements 
specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, as 
applicable; and repeat the inspection thereafter at the applicable 
intervals specified in Table 2, ``Reinspection Intervals for Part 
2--HFEC Inspection'' included in Figure 1 of the service bulletin.
    (i) If no cracking is detected and the fastener hole diameter is 
less than or equal to 0.5322 inch, before further flight, rework the 
hole in accordance with Part 3 of the Accomplishment Instructions of 
the service bulletin.
    (ii) If no cracking is detected and the fastener hole diameter 
is greater than 0.5322 inch, before further flight, accomplish the 
requirements specified in either paragraph (h)(1) or (h)(2) of this 
AD.
    (g) For airplanes on which the two aft-most fasteners have been 
inspected in accordance with Boeing Service Bulletin 767-54A0101, 
Revision 1, dated February 3, 2000, prior to May 15, 2001: Perform 
the initial inspection of the four aft-most fasteners in accordance 
with paragraph (f) of this AD before the accumulation of 10,000 
total flight cycles, or within 1,500 flight cycles after May 15, 
2001, whichever occurs later.

Corrective Actions

    (h) If any cracking is detected after accomplishment of any 
inspection required by paragraph (f) of this AD, before further 
flight, accomplish the requirements specified in either paragraph 
(h)(1) or (h)(2) of this AD.
    (1) Accomplish the terminating action specified in Part 4 of the 
Accomplishment Instructions of Boeing Service Bulletin 767-54A0101, 
Revision 1, dated February 3, 2000; Boeing Service Bulletin 767-
54A0101, Revision 3, dated September 5, 2002; or Boeing Alert 
Service Bulletin 767-54A0101, Revision 4, dated February 10, 2005. 
Accomplishment of this paragraph terminates the requirements of this 
AD. After the effective date of this AD, only Boeing Alert Service 
Bulletin 767-54A0101, Revision 4, may be used.
    (2) Replace the midspar fitting of the strut with a serviceable 
part, or repair in accordance with a method approved by the Manager, 
Seattle Aircraft Certification Office (ACO), FAA. Repeat the 
applicable inspection thereafter at the applicable time specified in 
paragraph (f)(1) or (f)(2) of this AD.
    (i) If any discrepancies (cracking, incorrect fastener hole 
diameter) are detected during any inspection required by paragraph 
(f) or (p) of this AD, for which the service bulletin specifies that 
the manufacturer may be contacted for disposition of those repair 
conditions: Before further flight, accomplish the applicable related 
investigative and corrective actions (including fastener hole rework 
and/or midspar fitting replacement) according to a method approved 
by the Manager, Seattle ACO; or in accordance with data meeting the 
certification basis of the airplane approved by an Authorized 
Representative for the Boeing Delegation Option Authorization 
Organization who has been authorized by the Manager, Seattle ACO, to 
make such findings. For a method to be approved, the approval must 
specifically reference this AD.

Additional Inspections

    (j) Prior to the accumulation of 10,000 total flight cycles, or 
within 600 flight cycles after June 9, 2004 (the effective date of 
AD 2004-09-14), whichever occurs later: Perform the inspections 
specified in paragraph (f)(1) or (f)(2) of this AD, as applicable, 
on all eight aft-most fastener holes or the four forward fastener 
holes in the group of eight aft-most fastener holes not inspected 
per paragraph (f)(1), (f)(2), or (g) of this AD. The inspection must 
be done per the Accomplishment Instructions in Boeing Service 
Bulletin 767-54A0101, Revision 3, dated September 5, 2002; or Boeing 
Alert Service Bulletin 767-54A0101, Revision 4, dated February 10, 
2005. Accomplishment of the applicable inspection on all eight aft-
most fastener holes constitutes terminating action for the 
repetitive inspection requirements of paragraphs (f)(1), (f)(2), and 
(g) of this AD.
    (k) If no cracking or discrepancy is detected during any 
detailed inspection required by paragraph (j) of this AD, repeat the 
inspections of all eight aft-most fastener holes thereafter at the 
applicable intervals specified in Table 1 of this AD.
    (l) If no cracking or discrepancy is detected during any HFEC 
inspection required by paragraph (j) of this AD or by this paragraph 
of this AD: Perform the follow-on actions specified in paragraph 
(f)(2)(i) or (f)(2)(ii) of this AD, as applicable, per the 
Accomplishment Instructions in Boeing Service Bulletin 767-54A0101, 
Revision 3, dated September 5, 2002; or Boeing Alert Service 
Bulletin 767-54A0101, Revision 4, dated February 10, 2005; and 
repeat the inspections of all eight aft-most fastener holes 
thereafter at the applicable intervals specified in Table 1 of this 
AD.

[[Page 32532]]



    Table 1.--Repetitive Inspection Intervals for All Eight Aft-Most
                             Fastener Holes
------------------------------------------------------------------------
                  If--                        Repetitive intervals--
------------------------------------------------------------------------
(1) All eight aft-most fastener holes    At the applicable intervals
 were inspected per paragraph (j) of      specified in Table 1,
 this AD:                                 ``Reinspection Intervals for
                                          Part 1,'' or Table 2,
                                          ``Reinspection Intervals for
                                          Part 2,'' as applicable. Both
                                          tables are included in Figure
                                          1 of the applicable service
                                          bulletin.
                                         Within 1,500 flight cycles
                                          after the effective date of
                                          this AD, only the repetitive
                                          intervals in Boeing Alert
                                          Service Bulletin 767-54A0101,
                                          Revision 4, dated February 10,
                                          2005, may be used.
(2) Only the four forward fastener       At the next scheduled
 holes in the group of eight aft-most     repetitive inspection required
 fastener holes were inspected per        by paragraph (f)(1) or (f)(2)
 paragraph (j) of this AD:                of this AD, as applicable.
                                          Thereafter at the applicable
                                          intervals specified in Table
                                          1, ``Reinspection Intervals
                                          for Part 1,'' or Table 2,
                                          ``Reinspection Intervals for
                                          Part 2,'' as applicable. Both
                                          tables are included in Figure
                                          1 of the applicable service
                                          bulletin.
                                         Within 1,500 flight cycles
                                          after the effective date of
                                          this AD, only the repetitive
                                          intervals in Boeing Alert
                                          Service Bulletin 767-54A0101,
                                          Revision 4, dated February 10,
                                          2005, may be used.
------------------------------------------------------------------------

Corrective Actions for Discrepancies

    (m) If any cracking or discrepancy is detected during any 
inspection required by paragraphs (j), (k), or (l) of this AD, 
before further flight: Accomplish the corrective actions described 
in paragraph (h) of this AD, except as provided in paragraph (i) of 
this AD.

Service Bulletin Revisions

    (n) Accomplishing the terminating action in paragraph (h)(1) of 
this AD before June 9, 2004 (the effective date of AD 2004-09-14) in 
accordance with the service bulletin revisions in Table 2 of this 
AD, is acceptable for compliance with the requirements of this AD. 
After the effective date of this AD, only Boeing Alert Service 
Bulletin 767-54A0101, Revision 4, dated February 10, 2005, may be 
used for accomplishing the terminating action in paragraph (h)(1) of 
this AD.

                           Table 2.--Service Bulletin Revisions for Terminating Action
----------------------------------------------------------------------------------------------------------------
        Boeing service bulletin                       Revision                               Date
----------------------------------------------------------------------------------------------------------------
767-54A0101...........................  Original...........................  September 23, 1999.
767-54A0101...........................  2..................................  January 10, 2002.
----------------------------------------------------------------------------------------------------------------

Inspections Accomplished per Previous Issues of Service Bulletin

    (o) Inspections required by paragraphs (f) and (g) of this AD 
that are accomplished before June 9, 2004 in accordance with the 
service bulletin revisions in Table 3 of this AD are considered 
acceptable for compliance with the corresponding action specified in 
this AD.

    Table 3.--Service Bulletin Revisions for Previously Accomplished
                               Inspections
------------------------------------------------------------------------
    Boeing service bulletin       Revision              Date
------------------------------------------------------------------------
767-54A0101....................          2  January 10, 2002.
767-54A0101....................          3  September 5, 2002.
767-54A0101....................          4  February 10, 2005.
------------------------------------------------------------------------

New Requirements of This AD

Inspections of Closeout Angle and Corrective Action

    (p) For airplanes for which the ``Reinspection Intervals for 
Part 1,'' referenced in Table 1 of paragraph (l) of this AD apply: 
At the next applicable inspection, do an HFEC inspection for cracks 
of the closeout angle that covers the two aft-most fasteners in the 
lower tang of the midspar fitting and any related investigative and 
corrective actions, by doing all the applicable actions specified in 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
767-54A0101, Revision 4, dated February 10, 2005. Repeat the 
inspection at the applicable interval in Table 1, ``Reinspection 
Intervals for Part 1,'' in Figure 1 of the alert service bulletin.

    Note 2: Boeing Alert Service Bulletin 767-54A0101, Revision 4, 
dated February 10, 2005, refers to the Boeing service bulletins in 
the Table 4 of this AD as additional sources of service information 
for doing the terminating action in paragraph (h)(1) of this AD.


                               Table 4.--Additional Sources of Service Information
----------------------------------------------------------------------------------------------------------------
       Boeing service bulletin              Revision level                Date                    Title
----------------------------------------------------------------------------------------------------------------
767-54-0052..........................  Original...............  June 11, 1992..........  Nacelles/Pylons--Strut--
                                                                                          Aft Lower Spar--
                                                                                          Fastener Corrosion--
                                                                                          Inspection and
                                                                                          Replacement.

[[Page 32533]]

 
767-54-0061..........................  2......................  November 23, 1999......  Nacelles/Pylons--Wing-
                                                                                          to-Strut Attach
                                                                                          Fittings--Lower Spar
                                                                                          Bushing Inspection and
                                                                                          Replacement.
767-54-0069..........................  2......................  August 31, 2000........  Nacelles/Pylons--
                                                                                          Midspar Fitting--
                                                                                          Underwing Sideload
                                                                                          Fitting--Fuse Pin
                                                                                          Replacement and Wing
                                                                                          Rework.
767-54-0072..........................  Original...............  March 13, 1997.........  Nacelles/Pylons--Strut
                                                                                          Attach Upper Link--
                                                                                          Upper Link Inspection,
                                                                                          Rework, or
                                                                                          Replacement.
767-54-0074..........................  Original...............  March 27, 1997.........  Nacelles/Pylons--Strut
                                                                                          Attach Fuse Pins--
                                                                                          Upper link Fuse Pin
                                                                                          Inspection/
                                                                                          Replacement. Where
                                                                                          this service bulletin
                                                                                          refers to a cotter pin
                                                                                          with part number (P/N)
                                                                                          MS 25665-374, the P/N
                                                                                          should be MS24665-374.
                                                                                          Where this service
                                                                                          bulletin says, ``If no
                                                                                          crack indication is
                                                                                          found, reinstall the
                                                                                          fuse pin,'' the
                                                                                          correct statement is
                                                                                          ``If no crack
                                                                                          indication is found,
                                                                                          continue to Step F.''
767-54-0080..........................  1......................  May 9, 2002............  Nacelles/Pylons--Pratt
                                                                                          and Whitney Powered
                                                                                          Airplanes--Nacelle
                                                                                          Strut and Wing
                                                                                          Structure
                                                                                          Modification.
767-54-0081..........................  1......................  February 7, 2002.......  Nacelles/Pylons--
                                                                                          General Electric
                                                                                          Powered Airplanes--
                                                                                          Nacelle Strut and Wing
                                                                                          Structure
                                                                                          Modification.
767-54A0062..........................  5......................  November 11, 2002......  Nacelles/Pylons--Strut
                                                                                          Attach Fuse Pins--
                                                                                          Midspar Fuse Pin
                                                                                          Inspection and
                                                                                          Replacement.
767-54A0094..........................  2......................  February 7, 2002.......  Nacelles/Pylons--Strut-
                                                                                          to-Wing Attachment--
                                                                                          Diagonal Brace
                                                                                          Inspection/Rework/
                                                                                          Replacement.
767-57-0063..........................  1......................  November 30, 2000......  Wings--Side Load
                                                                                          Underwing Fitting--
                                                                                          Inspection/Rework.
----------------------------------------------------------------------------------------------------------------


    Note 3: Certain service bulletins referenced in Table 4 of this 
AD are related to the ADs listed in Table 5 of this AD.


                                       Table 5.--Other Relevant Rulemaking
----------------------------------------------------------------------------------------------------------------
                                                                Related Boeing  service
                  AD                        Applicability               bulletin              AD requirement
----------------------------------------------------------------------------------------------------------------
AD 94-11-02, amendment 39-8919, (59    All Boeing Model 767     767-54A0062............  Repetitive detailed
 FR 27229, June 10, 1994).              series airplanes.                                 visual and eddy
                                                                                          current inspections to
                                                                                          detect cracks of
                                                                                          certain midspar fuse
                                                                                          pins, and replacement
                                                                                          of any cracked midspar
                                                                                          fuse pin with a new
                                                                                          fuse pin.
AD 99-07-06, amendment 39-11091 (64    Certain Boeing Model     767-54A0094............  Repetitive inspections
 FR 14578, March 26, 1999).             767 series airplanes.                             to detect cracking or
                                                                                          damage of the forward
                                                                                          and aft lugs of the
                                                                                          diagonal brace of the
                                                                                          nacelle strut; follow-
                                                                                          on actions, if
                                                                                          necessary; and an
                                                                                          optional terminating
                                                                                          action for the
                                                                                          repetitive
                                                                                          inspections.
                                                                                          Superseded by AD 2000-
                                                                                          07-05.
AD 2000-07-05, amendment 39-11659 (65  Certain Boeing Model     767-54A0094............  Requires the previously
 FR 18883, April 10, 2000).             767 series airplanes.                             optional terminating
                                                                                          action of AD 99-07-06.

[[Page 32534]]

 
AD 2000-10-15, amendment 39-11770 (65  Certain Boeing Model     767-54-0074............  One-time inspection to
 FR 37011, June 13, 2000).              767 series airplanes.                             determine whether
                                                                                          certain bolts are
                                                                                          installed in the side
                                                                                          load underwing
                                                                                          fittings on both
                                                                                          struts, and various
                                                                                          follow-on actions, if
                                                                                          necessary.
AD 2001-02-07, amendment 39-12091 (66  Certain Boeing Model     767-54-0069, 767-54-     Modification of the
 FR 8085, January 29, 2001).            767 series airplanes     0080, and 767-54A0094.   nacelle strut and wing
                                        powered by Pratt &                                structure. Terminates
                                        Whitney engines.                                  certain requirements
                                                                                          of AD 94-11-02.
AD 2001-06-12, amendment 39-12159 (66  Certain Boeing Model     767-54-0069, 767-54-     Modification of the
 FR 17492, April 2, 2001).              767 series airplanes     0081, and 767-54A0094.   nacelle strut and wing
                                        powered by General                                structure. Terminates
                                        Electric engines.                                 certain requirements
                                                                                          of AD 94-11-02.
AD 2003-03-02, amendment 39-13026 (68  All Boeing Model 767     767-54A0062............  Supersedes AD 94-11-02;
 FR 4374, January 29, 2003).            series airplanes.                                 Retains all
                                                                                          requirements but
                                                                                          reduces certain
                                                                                          compliance times for
                                                                                          certain inspections,
                                                                                          expands the detailed
                                                                                          and eddy current
                                                                                          inspections,and limits
                                                                                          the applicability.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (q)(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) AMOCS approved previously according to AD 2004-09-14, 
amendment 39-13603, are approved as AMOCs for the corresponding 
requirements of this AD.
    (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 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 May 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-11050 Filed 6-2-05; 8:45 am]
BILLING CODE 4910-13-P