Airworthiness Directives; Boeing Model 747-100, -200B, -200F, -200C, -100B, -300, -100B SUD, -400, -400D, and -400F Series Airplanes; and Model 747SR Series Airplanes, 19345-19351 [05-7380]

Download as PDF Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Proposed Rules 19345 Actions Compliance Procedures (3) Remove the Temporary Revision to the POH specified in paragraph (e)(1) of this AD after the pitch actuator is replaced as required in paragraph (e)(2) of this AD. Before further flight after the pitch actuator is replaced with an improved design pitch actuator. (4) Do not install a P/N 985.92.03.161 pitch actuator. As of the effective date of this AD ................... The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may modify the POH as specified in paragraph (e)(3) of of this AD. Make an entry into the aircraft records showing compliance with this portion of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). Not applicable. May I Request an Alternative Method of Compliance? DEPARTMENT OF TRANSPORTATION (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; facsimile: (816) 329–4090. Federal Aviation Administration Is There Other Information That Relates to This Subject? (g) Swiss AD Number HB–2005–128, effective date March 29, 2005, also addresses the subject of this AD. May I Get Copies of the Documents Referenced in this AD? (h) To get copies of the documents referenced in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; e-mail: SupportPC12@pilatus-aircraft.com or from Pilatus Business Aircraft Ltd., Product Support Department, 11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465–9099; facsimile: (303) 465–6040. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC, or on the Internet at https://dms.dot.gov. This is docket number FAA–2005–20720; Directorate Identifier 2005–CE–17–AD. Issued in Kansas City, Missouri, on April 6, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–7382 Filed 4–12–05; 8:45 am] BILLING CODE 4910–13–P VerDate jul<14>2003 15:00 Apr 12, 2005 Jkt 205001 14 CFR Part 39 [Docket No. FAA–2005–20917; Directorate Identifier 2004–NM–85–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100, –200B, –200F, –200C, –100B, –300, –100B SUD, –400, –400D, and –400F Series Airplanes; and Model 747SR Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede two existing airworthiness directives (AD) for certain Boeing transport category airplanes. One AD currently requires doing certain inspections to detect cracks and corrosion around the lower bearing of the actuator attach fittings of the inboard and outboard flaps; repairing if necessary; and either overhauling the fittings or replacing them, which when done on certain actuator attach fittings ends the repetitive inspections. The other AD currently requires certain other inspections to detect discrepancies of the fittings of the flaps, and follow-on and corrective actions if necessary, which ends the repetitive inspections of the first AD. For certain airplanes, this proposed AD would require new inspections for discrepancies of the attach fittings of the flaps, and follow-on and corrective actions if necessary, which ends the repetitive inspections of both existing ADs. For all airplanes, this proposed AD would require repetitive overhaul/ replacements of the fittings of both the inboard and outboard flaps. This proposed AD is prompted by reports of cracks of the attach fittings of the trailing edge flaps. We are proposing this AD to prevent cracking and other damage of the actuator attach fittings of PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 the trailing edge flaps, which could result in abnormal operation or retraction of a trailing edge flap, and possible loss of controllability of the airplane. DATES: We must receive comments on this proposed AD by May 31, 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 https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You can get the service information identified in this proposed AD from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. You may examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or 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. FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6443; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Docket Management System (DMS) The FAA has implemented new procedures for maintaining AD dockets electronically. As of May 17, 2004, new AD actions are posted on DMS and assigned a docket number. We track E:\FR\FM\13APP1.SGM 13APP1 19346 Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Proposed Rules each action and assign a corresponding directorate identifier. The DMS AD docket number is in the form ‘‘Docket No. FAA–2004–99999.’’ The Transport Airplane Directorate identifier is in the form ‘‘Directorate Identifier 2004–NM– 999–AD.’’ Each DMS AD docket also lists the directorate identifier (‘‘Old Docket Number’’) as a cross-reference for searching purposes. Comments Invited We invite you to submit any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20917; Directorate Identifier 2004–NM–85–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of 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 may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. We are reviewing the writing style we currently use in regulatory documents. We are interested in your comments on whether the style of this document is clear, and your suggestions to improve the clarity of our communications that affect you. You can get more information about plain language at https://www.faa.gov/language and https:// www.plainlanguage.gov. Examining the Docket You may examine the AD docket 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 VerDate jul<14>2003 15:00 Apr 12, 2005 Jkt 205001 the AD docket shortly after the DMS receives them. Discussion On June 20, 2001, we issued AD 2001–13–12, amendment 39–12292 (66 FR 34526, June 29, 2001), for certain Boeing Model 747 series airplanes. That AD requires repetitive inspections to detect cracks and corrosion around the lower bearing of the actuator attach fittings of the inboard and outboard flaps. That AD also requires repetitive overhauls for certain actuator attach fittings or repetitive replacement of the fittings with new fittings, as applicable, which terminates the repetitive inspections. That AD also provides for replacement of actuator attach fittings with improved fittings, which terminates all requirements of that AD. That AD was prompted by reports of cracks on the lower bearing journal of the inboard actuator attach fittings of the outboard trailing edge flaps due to stress corrosion. We issued that AD to detect and correct cracking on the actuator attach fittings of the trailing edge flaps, which could result in abnormal operation or retraction of a trailing edge flap, and consequent reduced controllability of the airplane. On April 14, 2003, we issued AD 2003–08–11, amendment 39–13124 (68 FR 19937, April 23, 2003), for all Boeing Model 747–100, –200B, –200F, –200C, –100B, –300, –100B SUD, –400, –400D, and –400F series airplanes; and Model 747SR series airplanes. That AD requires repetitive inspections to detect discrepancies of the actuator attach fittings of the inboard and outboard flaps, which are more comprehensive than those required by AD 2001–13–12, and follow-on and corrective actions as necessary. That AD was prompted by reports of three fractures of the attach fittings of the trailing edge flap actuator. We issued that AD to detect and correct cracking and other damage of the actuator attach fittings of the trailing edge flaps, which could result in abnormal operation or retraction of a trailing edge flap, and possible loss of controllability of the airplane. In the preamble of AD 2003–08–11, we indicated that the actions required by that AD were considered ‘‘interim action,’’ and that further rulemaking action was being considered to require repetitive replacement of the fittings with new or overhauled fittings. We now have determined that further rulemaking action is indeed necessary, and this proposed AD follows from that determination. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Relevant Service Information We have previously reviewed Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002 (cited in AD 2003–08–11 as the appropriate source of service information for the required actions). The service bulletin describes procedures for repetitive inspections of the attach fittings of the inboard and outboard flaps to detect discrepancies (i.e., Part 1). The inboard fittings are to be inspected using borescopic and detailed visual methods; and the outboard fittings are to be inspected using borescopic, detailed visual, and ultrasonic methods. The service bulletin also describes procedures for repetitive detailed visual (inboard and outboard flaps) and ultrasonic (outboard flap only) inspections with the attach fittings removed to detect discrepancies (i.e., Part 2). Discrepancies include surface corrosion, pitting, cracks, migrated or rotated bushings, and damaged or missing cadmium plating. The service bulletin also describes procedures for corrective and follow-on actions if necessary (i.e., Parts 3 through 5), which includes repetitive detailed visual inspections to detect bushing migration and cracking and other damage of the actuator attach fittings; repetitive application of corrosion-inhibiting compound; and repetitive overhaul or replacement of any discrepant fitting with a new or overhauled fitting; as applicable. Repetitive overhauls of the attach fittings on the outboard and inboard flaps or repetitive replacements of those attach fittings with new or overhauled fittings (i.e., Part 5) ends the need for repetitive inspections. The manufacturer advises that Boeing Alert Service Bulletin 747–57A2316 replaces Boeing Alert Service Bulletin 747–57A2310 (cited as the appropriate source of service information for the requirements of AD 2001–13–12). We have determined that accomplishing the actions specified in Boeing Service Bulletin 747–57A2316 will adequately address the unsafe condition. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. Therefore, we are proposing this AD, which would supersede ADs 2001–13–12 and 2003– 08–11. This proposed AD would continue to require the following actions specified in AD 2001–13–12: • Repetitive inspections to detect cracks and corrosion around the lower bearing of the actuator attach fittings of E:\FR\FM\13APP1.SGM 13APP1 Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Proposed Rules found on either the inboard or outboard flap; • Part 3: Repetitive intervals of 9 months (for inboard flaps only); • Part 4: Repetitive intervals of 9 months (for outboard flaps only); and • Part 5: Ranges from before the attach fitting is 8 years old, or within 2 years, whichever occurs first, to 3 years depending on the age of the outboard and inboard attach fittings. If any crack, corrosion, or damaged cad plating is found on either the inboard or outboard flap, the compliance time is before further flight. the inboard and outboard flaps, and repair if necessary; and • Repetitive overhauls of the actuator attach fittings on the outboard flaps and a one-time overhaul of the fittings on the inboard flaps, which ends the applicable repetitive inspections described previously; or repetitive replacements of the fittings on the inboard and outboard flaps with new fittings or a one-time replacement of those fittings with improved fittings, which ends the repetitive inspections described previously. In addition, this proposed AD would continue to require the following actions specified in AD 2003–08–11: Repetitive inspections to detect discrepancies of the actuator attach fittings of the inboard and outboard flaps (i.e., Part 1) and follow-on/ corrective actions as necessary (i.e, Parts 2 and 5). Accomplishing the initial inspections (i.e., Part 1) would end the repetitive inspections around the lower bearing of the fittings of the inboard and outboard flaps described previously. This proposed AD would also require the actions specified in Parts 2 through 5 of Boeing Alert Service Bulletin 747– 57A2316 described previously, except as discussed under ‘‘Difference Between the Proposed AD and the Service Bulletin.’’ Accomplishing the actions in Part 2 of the service bulletin ends the inspections specified in Part 1 of the service bulletin. Accomplishing the actions in Part 5 of the service bulletin (i.e. repetitive overhauls or replacements of the attaching fittings at intervals not to exceed 8 years) ends all repetitive inspections for both inboard and outboard actuator attach fittings over eight years old. The compliance times are as follows: • Part 1: 90 days (for inboard and outboard flaps); • Part 2: 9 months (for inboard flaps), 18 months (for outboard flaps), and before further flight if any crack, corrosion, or damaged cad plating is Difference Between the Proposed AD and the Service Bulletin Boeing Alert Service Bulletin 747– 57A2316 refers to ‘‘detailed visual inspection’’ for discrepancies of the actuator attach fittings of the inboard and outboard flaps. We have determined that the procedures in the service bulletin should be described as a ‘‘detailed inspection.’’ Note 1 has been included in this proposed AD to define this type of inspection. Change to Existing ADs This proposed AD would retain all requirements of ADs 2001–13–12 and 2003–08–11. Since those ADs were 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 two tables: REVISED PARAGRAPH IDENTIFIERS Corresponding requirement in this proposed AD Requirement in AD 2001–13–12 paragraph paragraph paragraph paragraph paragraph paragraph (a) ............ (b) ............ (c) ............ (d) ............ (e) ............ (f) ............. paragraph paragraph paragraph paragraph paragraph paragraph (g) (h) (i) (j) (k) (l) Requirement in AD 2003–08–11 paragraph paragraph paragraph paragraph (a) (b) (c) (d) ............ ............ ............ ............ 19347 Corresponding requirement in this proposed AD paragraph paragraph paragraph paragraph (m) (n) (o) (p) We also have changed all references to a ‘‘detailed visual inspection’’ in the existing ADs to ‘‘detailed inspection’’ in this action. In addition, we have added a new requirement that, as of the effective date of this AD, the repetitive overhauls and replacements in paragraphs (j)(1) and (k)(1) of this proposed AD (paragraphs (d) and (e)(1) of AD 2001–13–12), respectively, must be done in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002, at intervals not to exceed 8 years. The repetitive intervals for those repetitive requirements in AD 2001–13–12 are 8 years or 8,000 flight cycles, whichever occurs first. Because corrosion is time dependant rather than flight-cycle dependant, we determined that the intervals for the repetitive overhauls and replacements should be based on time only. We also determined that operators should accomplish those actions in accordance with the latest service bulletin. Costs of Compliance This proposed AD would affect about 1,000 Model 747–100, –200B, –200F, –200C, –100B, –300, –100B SUD, –400, –400D, and –400F series airplanes; and Model 747SR series airplanes worldwide. There are about 181 airplanes on the U.S. registry. The average labor rate is $65 per hour. The following two tables provide the estimated costs for U.S. operators to comply with this proposed AD. TABLE 1.—ESTIMATED COSTS Work hours Action Inspections (required by AD 2001– 13–12). Inspections specified in Part 1 of the Accomplishment Instruction (AI) of the referenced service bulletin (required by AD 2003–08– 11). Inspections specified in Part 2 of the AI of the referenced service bulletin (new proposed actions). VerDate jul<14>2003 15:00 Apr 12, 2005 Jkt 205001 Parts Cost per airplane 2 None ................... $130, per inspection cycle .............. $23,530, per inspection cycle. 2 None ................... $130 per inspection cycle ............... $23,530 per inspection cycle. 5 None ................... $325 per inspection cycle ............... $58,825 per inspection cycle. PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\13APP1.SGM Fleet cost 13APP1 19348 Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Proposed Rules TABLE 2.—ESTIMATED COSTS Action Work hours Overhaul(s) as an alternative to the replacement. Replacement(s) as an alternative to the overhaul. Parts Cost per airplane 37 None ........................................................................ $2,405. 4 $6,623 (for the four attach fittings on the outboard flaps) and $7,566 (for the four attach fittings on the inboard flaps). $6,883 (for the four attach fittings on the outboard flaps) and $7,826 (for the four attach fittings on the inboard flaps), per replacement cycle. Authority for This Rulemaking List of Subjects in 14 CFR Part 39 Requirements of AD 2001–13–12 Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Air transportation, Aircraft, Aviation safety, Safety. Affected Airplanes 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. VerDate jul<14>2003 16:40 Apr 12, 2005 Jkt 205001 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (f) For Boeing Model 747 series airplanes, as listed in Boeing Service Bulletin 747– 57A2310, Revision 2, dated February 22, 2001, do the actions required by paragraphs (g) through (l) of this AD, as applicable. Actuator Attach Fittings That Have Not Been Overhauled or Replaced Boeing: Docket No. FAA–2005–20917; Directorate Identifier 2004–NM–85–AD. (g) For actuator attach fittings on the outboard flaps that have not been overhauled in accordance with revisions of Boeing 747 Overhaul Manual (OHM) 57–52–55 dated prior to June 1, 1999, or replaced with a new fitting, prior to August 3, 2001 (the effective date of AD 2001–13–12); and for actuator attach fittings on the inboard flap actuators that have not been overhauled in accordance with revisions of OHM 57–52–35, dated prior to June 1, 1999, or replaced with a new fitting, prior to August 3, 2001: Accomplish the actions in paragraph (i), (j), or (k) of this AD at the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Prior to the accumulation of 8 years since date of manufacture or 8,000 total flight cycles, whichever occurs first. (2) Within 6 months after August 3, 2001. Comments Due Date (a) The Federal Aviation Administration must receive comments on this airworthiness directive (AD) action by May 31, 2005. Actuator Attach Fittings That Have Been Overhauled or Replaced (h) For actuator attach fittings on the outboard flaps that have been overhauled in accordance with revisions of OHM 57–52–55 dated prior to June 1, 1999, or replaced with a new fitting, prior to August 3, 2001; and for actuator attach fittings on the inboard flap actuators that have been overhauled in accordance with revisions of OHM 57–52–35 dated prior to June 1, 1999, or replaced with a new fitting, prior to August 3, 2001: Accomplish the actions in paragraph (i), (j), or (k) of this AD at the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Within 8 years or 8,000 total flight cycles after the attach fitting was overhauled or replaced, whichever occurs first. (2) Within 6 months after August 3, 2001. 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 amendments 39–12292 (66 FR 34526, June 29, 2001) and 39–13124 (68 FR 19937, April 23, 2003) and adding the following new airworthiness directive (AD): Affected ADs (b) This AD supersedes AD 2001–13–12, amendment 39–12292; and AD 2003–08–11, amendment 39–13124. Applicability: (c) This AD applies to all Boeing Model 747–100, –200B, –200F, –200C, –100B, –300, –100B SUD, –400, –400D, and –400F series airplanes; and Model 747SR series airplanes; certificated in any category. Unsafe Condition (d) This AD was prompted by reports of cracks of the attach fittings of the trailing edge flaps. We are issuing this AD to prevent cracking and other damage of the actuator attach fittings of the trailing edge flaps, which could result in abnormal operation or retraction of a trailing edge flap, and possible loss of controllability of the airplane. Compliance: (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Inspections and Corrective Action (i) Perform a detailed inspection to detect corrosion around the lower bearing journal on the actuator attach fittings on the inboard and outboard flaps, and perform an ultrasonic inspection to detect cracks around the lower bearing journal of the actuator attach fittings on the outboard flaps, in accordance with Boeing Service Bulletin 747–57A2310, Revision 1, dated November E:\FR\FM\13APP1.SGM 13APP1 Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Proposed Rules 23, 1999; or Revision 2, dated February 22, 2001. 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.’’ Note 2: Inspections, overhauls, and replacements accomplished in accordance with Boeing Alert Service Bulletin 747– 57A2310, dated June 17, 1999, are acceptable for compliance with the requirements of paragraph (i) of this AD. (1) If no corrosion or cracks are detected, repeat the inspections required by paragraph (i) of this AD at intervals not to exceed 18 months. Within 5 years after the initial inspections required by paragraph (i) of this AD, accomplish the actions specified in paragraph (j) or (k) of this AD. (2) If any corrosion is detected, prior to further flight, remove the corrosion by accomplishing the actions of either paragraph (i)(2)(i) or (i)(2)(ii) of this AD. (i) If corrosion is within the limits of the Boeing 747 OHM: Prior to further flight, accomplish the actions specified in paragraph (j) or (k) of this AD. (ii) If corrosion is not within the limits of the Boeing 747 OHM: Prior to further flight, accomplish the actions specified in paragraph (k) or (l) of this AD. (3) If any crack is detected: Prior to further flight, accomplish the actions specified in paragraph (k) or (l) of this AD. Overhaul (j) Do the actions as specified in paragraphs (j)(1) and (j)(2) of this AD in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–57A2310, Revision 1, dated November 23, 1999; or Revision 2, dated February 22, 2001. (1) Overhaul the actuator attach fittings on the outboard flaps. Repeat the overhaul of actuators on the outboard flaps as specified in Part 2 of the Work Instructions of the service bulletin thereafter at intervals not to exceed 8 years or 8,000 flight cycles, whichever occurs first. As of the effective date of this AD, the repetitive overhauls must be done in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002, at intervals not to exceed 8 years since last overhaul. Accomplishment of the overhaul of the actuator attach fittings on the outboard flaps constitutes terminating action for the repetitive inspection requirements of paragraph (i)(1) of this AD for outboard flaps. (2) Overhaul the actuator attach fittings on the inboard flaps. Accomplishment of the overhaul of the actuator attach fittings on the inboard flaps constitutes terminating action for the requirements of paragraphs (g) through (l) of this AD for the actuator attach fittings on the inboard flaps. VerDate jul<14>2003 15:00 Apr 12, 2005 Jkt 205001 Replacement (k) Replace the actuator attach fittings on the inboard and outboard flaps in accordance with paragraph (k)(1) or (k)(2) of this AD. (1) Replace the actuator attach fittings on the inboard and outboard flaps with new attach fittings in accordance with ‘‘Part 3— Replacement’’ of Boeing Service Bulletin 747–57A2310, Revision 1, dated November 23, 1999; or Revision 2, dated February 22, 2001. Accomplishment of this replacement constitutes terminating action for the repetitive inspections required by paragraph (i) of this AD for the replaced fitting. Within 8 years or 8,000 flight cycles following accomplishment of the replacement, whichever occurs first, repeat this replacement or accomplish the overhaul specified in paragraph (j) of this AD. As of the effective date of this AD, the repetitive replacements must be done in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002, at intervals not to exceed 8 years since last replacement. (2) Replace the actuator attach fittings on the inboard and outboard flaps with improved attach fittings in accordance with ‘‘Part 4—Terminating Action’’ of Boeing Service Bulletin 747–57A2310, Revision 2, dated February 22, 2001. If accomplished, this replacement with improved fittings terminates the requirements of paragraphs (g) through (l) of this AD for the replaced fitting. Note 3: Replacement of the actuator attach fittings on the inboard flaps with fittings that have been overhauled before the effective date of this AD, in accordance with Boeing OHM 57–52–35, Temporary Revision 57–8, dated June 10, 1999; Temporary Revision 57– 10, dated May 8, 2000; or Full Revision 57– 10, dated July 1, 2000; constitutes terminating action for the requirements of paragraphs (g) through (l) of this AD for the actuator attach fittings on the inboard flaps. Repair (l) During any inspection done in accordance with paragraph (i) of this AD, if corrosion is found that is outside the limits specified in the Boeing 747 OHM, or if any crack is detected: In lieu of replacement of the actuator attach fittings in accordance with paragraph (k) of this AD, repair the actuator attach fittings on the inboard and outboard flaps in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or per data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager’s approval letter must specifically reference this AD. Requirements of AD 2003–08–11 Inspection: Inboard Flap Attach Fittings (m) Perform borescopic and detailed inspections to detect discrepancies of the inboard flap attach fittings, in accordance with Part 1 of the Accomplishment PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 19349 Instructions of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002. Discrepancies include corrosion, pitting, and damaged or missing cadmium plating. Do the inspection at the applicable time specified in paragraph (m)(1) or (m)(2) of this AD. (1) If the age of the fittings can be determined: Inspect within 14 years since the fittings were new or last overhauled, or within 90 days after May 8, 2003 (the effective date of AD 2003–08–11), whichever occurs later. (2) If the age of the fittings cannot be determined: Inspect within 90 days after May 8, 2003. Note 4: The exceptions specified in flag note 4 of Figure 1 of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002, apply to the requirements of paragraphs (m) and (n) of this AD. Inspection: Outboard Flap Attach Fittings (n) Perform borescopic, detailed, and ultrasonic inspections to detect discrepancies of the outboard flap attach fittings, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002. Discrepancies include surface corrosion, pitting, damaged or missing cadmium plating, and cracks. Do the inspection at the applicable time specified in paragraph (n)(1) or (n)(2) of this AD. (1) If the age of the fittings can be determined: Inspect within 8 years since the fittings were new or last overhauled, or within 90 days May 8, 2003, whichever occurs later. (2) If the age of the fittings cannot be determined: Inspect within 90 days after May 8, 2003. Follow-on Actions: No Discrepancies Found (o) If no discrepancy is found during any inspection required by paragraph (m) or (n) of this AD: Do the actions specified by either paragraph (o)(1) or paragraph (o)(2) of this AD. (1) Repeat the applicable inspections specified in paragraphs (m) and (n) of this AD at intervals not to exceed 9 months until the actions specified in paragraph (o)(2) of this AD have been accomplished. (2) Perform a detailed inspection of the fitting to detect cracks, corrosion, damaged cadmium plating, or bushing migration, in accordance with and at the time specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002. Do the follow-on actions in accordance with Parts 3, 4, and 5 of the Accomplishment Instructions of the service bulletin at the times specified in Figure 1 of the service bulletin, as applicable. Accomplishment of these actions terminates the initial and repetitive inspection requirements of paragraphs (m), (n), and (o)(1) of this AD. Note 5: The exceptions specified in flag note 2 of Figure 1 of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002, apply to those requirements of paragraphs (o)(2) and (p) of this AD that are specified in Part 2 of the service bulletin. E:\FR\FM\13APP1.SGM 13APP1 19350 Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Proposed Rules Corrective/Follow-on Actions: Discrepancies Found (p) If any discrepancy is found during any inspection required by paragraph (m), (n), or (o) of this AD: Perform applicable corrective and follow-on actions at the time specified and in accordance with Figure 1 of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002. Before further flight: Replace any discrepant fitting in accordance with Part 5 of the Accomplishment Instructions of the service bulletin, and accomplish the follow-on actions for the other fittings common to that flap in accordance with Part 2 of the Accomplishment Instructions of the service bulletin. Replacement of a fitting terminates the initial and repetitive inspections— specified in paragraphs (m), (n), and (o) of this AD—for that fitting only. Terminating Action for Certain Requirements (q) Accomplishment of the actions required by paragraphs (m) and (n) of this AD ends the requirements of paragraphs (g) through (k) of this AD, except for the repetitive overhauls and repetitive replacements required by paragraphs (j)(1) and (k)(1) of this AD, respectively. New Actions Required by This AD Inspections: Attach Fittings of the Inboard and Outboard Flaps (r) For airplanes on which the repetitive borescopic, detailed, or ultrasonic (as applicable) inspections required by paragraphs (m), (n), or (o)(1) of this AD are being done as of the effective date of this AD: Inspect as specified in Table 1 of this AD. Accomplishing these actions ends the initial and repetitive inspections required by paragraphs (m), (n), and (o)(1) of this AD. TABLE 1.—INSPECTIONS OF ATTACH FITTINGS Requirements Description (1) Compliance time ........................................... Except as provided by paragraph (u) of this AD, at the applicable time specified in Figure 1 of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002. The attach fittings of the inboard and outboard flaps. Detailed inspection (inboard and outboard flaps) and ultrasonic inspection (outboard flaps only). Surface corrosion, pitting, cracks, migrated or rotated bushings, and damaged or missing cadmium plating. Part 2 of the Work Instructions of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002. (2) Area to inspect .............................................. (3) Type of inspection ........................................ (4) Discrepancies to detect ................................ (5) In accordance with ........................................ Follow-on Actions: No Discrepancies Detected (s) If no discrepancy is detected during any inspection required by paragraph (r) of this AD: Do the follow-on actions in accordance with Parts 3, 4, and 5, as applicable, of the Work Instructions of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002, at the applicable times specified in Figure 1 of the service bulletin, except as provided by paragraph (u) of this AD. Overhaul/Replacement and Follow-on/ Corrective Actions: Discrepancies Detected this AD: Do the actions specified in Table 2 of this AD at the applicable times specified in Figures 1 and 2 of the service bulletin, except as provided by paragraph (v) of this AD. (t) If any discrepancy is detected during any inspection required by paragraph (r) of TABLE 2.—DISCREPANCIES FOUND In accordance with Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002— Requirements (1) Overhaul or replace discrepant fitting with new fitting ....................... (2) Do the follow-on and corrective actions for the other fitting common to that flap, except as specified in flag note 2 in Figure 1 of the service bulletin. Compliance Time Requirements (u) For the requirements of paragraph (r) of this AD: Where Figure 1 of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002, states a compliance time ‘‘after the original issue date of the service bulletin,’’ this AD requires compliance within the applicable compliance time after the effective date of this AD. (v) For the requirements of paragraph (s) of this AD: Where Figure 1 of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002, specifies to repeat the overhaul or replacement ‘‘every 8 years,’’ this AD requires compliance at intervals not to exceed 8 years. Repetitive Overhaul or Replacement (w) Except as provided in paragraph (x) of this AD, at the applicable time specified in paragraph (w)(1) or (w)(2) of this AD, overhaul the attach fittings on the outboard and inboard flaps or replace the attach VerDate jul<14>2003 15:00 Apr 12, 2005 Jkt 205001 Part 5 of Work Instructions. Parts 2 and 5 of Work Instructions, as applicable. fittings with new or overhauled fittings, in accordance with Part 5 of the Work Instructions of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002. Repeat the overhaul or replacement thereafter at intervals not to exceed 8 years. (1) If the age of the fittings can be determined: Overhaul or replace within 8 years since the fittings were new or last overhauled, or within 2 years after the effective date of this AD, whichever occurs later. (2) If the age of the fittings cannot be determined: Assume that the fittings are more than 14 years old, and overhaul or replace within 2 years after the effective date of this AD. (x) Accomplishing the repetitive overhauls required by paragraph (j)(1) or repetitive replacements required by paragraph (k)(1) of this AD is acceptable for compliance with the requirements of paragraph (w) of this AD. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 Alternative Methods of Compliance (AMOCs) (y)(1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) 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. (3) AMOCs approved previously in accordance with AD 2001–13–12 are approved as AMOCs with the actions required by paragraphs (g) through (l) of this AD, as applicable. However, AMOCs approved previously are not considered E:\FR\FM\13APP1.SGM 13APP1 Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Proposed Rules terminating action for the repetitive overhauls or replacements requirements of this AD. (4) AMOCs approved previously in accordance with AD 2003–08–11 are approved as AMOCs with the actions required by paragraphs (m) through (p) of this AD, as applicable. Issued in Renton, Washington, on April 6, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–7380 Filed 4–12–05; 8:45 am] BILLING CODE 4910–13–P SOCIAL SECURITY ADMINISTRATION 20 CFR Parts 404 and 416 [Regulation Nos. 4 and 16] RIN 0960–AG21 New Medical Criteria for Evaluating Language and Speech Disorders Social Security Administration. Advance notice of proposed rulemaking. AGENCY: ACTION: SUMMARY: We are considering whether to propose new rules for evaluating language and speech disorders. The new rules would apply to adults and children who apply for, or receive, disability benefits under title II and Supplemental Security Income (SSI) payments based on disability under title XVI of the Social Security Act (the Act). Specifically, we are considering whether to add a new body system in the Listing of Impairments in appendix 1 to subpart P of part 404 of our regulations (the listings) for these disorders. We invite you to send us comments about whether we should establish these new rules, as well as suggestions about what the proposed rules should include. We will consider your comments and suggestions, as well as information about advances in medical knowledge, treatment, and methods of evaluating language and speech disorders, along with our program experience. If we decide to propose new listings for language and speech disorders, we will publish them as proposed rules for public comment in a Notice of Proposed Rulemaking (NPRM). As part of our long-term planning for the disability programs, we are also interested in your ideas for how we may improve our programs for people with disabilities, including people who have disabilities based on language and speech disorders, and especially those who would like to work. VerDate jul<14>2003 15:00 Apr 12, 2005 Jkt 205001 To be sure your comments are considered, we must receive them by June 13, 2005. ADDRESSES: You may give us your comments by: Using our Internet site facility (i.e., Social Security Online) at https://policy.ssa.gov/pnpublic.nsf/ LawsRegs or the Federal eRulemaking Portal at https://www.regulations.gov; email to regulations@ssa.gov; telefax to (410) 966–2830; or letter to the Commissioner of Social Security, P.O. Box 17703, Baltimore, Maryland 21235– 7703. You may also deliver them to the Office of Regulations, Social Security Administration, 107 Altmeyer Building, 6401 Security Boulevard, Baltimore, Maryland 21235–6401, between 8 a.m. and 4:30 p.m. on regular business days. Comments are posted on our Internet site at https://policy.ssa.gov/ pnpublic.nsf/LawsRegs, or you may inspect them on regular business days by making arrangements with the contact person shown in this preamble. Electronic Version: The electronic file of this document is available on the date of publication in the Federal Register at https://www.gpoaccess.gov/fr/ index.html. It is also available on the Internet site for SSA (i.e., Social Security Online) at: https:// policy.ssa.gov/pnpublic.nsf/LawsRegs. FOR FURTHER INFORMATION CONTACT: Robert J. Augustine, Social Insurance Specialist, Office of Regulations, Social Security Administration 107 Altmeyer Building, 6401 Security Boulevard, Baltimore, Maryland 21235–6401, (410) 965–0020 or TTY (410) 966–5609. For information on eligibility or filing for benefits, call our national toll-free number 1–800–772–1213 or TTY 1– 800–325–0778, or visit our Internet Web site, Social Security Online, at https:// www.socialsecurity.gov. SUPPLEMENTARY INFORMATION: DATES: What Is the Purpose of This Notice? We are considering whether to add a new body system to our listings for evaluating language and speech disorders. The new listings would apply to adults and children who apply for, or receive, disability benefits under title II and Supplemental Security Income (SSI) payments based on disability under title XVI of the Act. The purpose of this notice is to give you an opportunity to send us comments about whether we should establish these new rules, and if so, suggestions about what these proposed rules should include. We are also asking for your comments and ideas about how we can improve our disability programs in the future for people with language and speech disorders. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 19351 Who Should Send Us Comments and Suggestions? We invite comments and suggestions from anyone who has an interest in how we evaluate claims for benefits in our disability programs that are filed by people who have language and speech disorders. We are interested in comments and suggestions from people who apply for or receive benefits from us, including people who have language or speech disorders. We are also interested in comments and suggestions from members of the general public, individuals and organizations that advocate for people who have language and speech disorders, speech-language pathologists, physicians, other health care professionals, researchers, vocational specialists, people who make disability determinations for us, and any other people who may have ideas for us to consider. Will We Respond to Your Comments From This Notice? No, we will not respond directly to comments you send us because of this notice. However, after we consider your comments along with other information, such as that gained from relevant textbooks and our disability program experience, we will decide whether to propose new rules for evaluating language and speech disorders. If we propose new rules, we will publish them in an NPRM in the Federal Register. In accordance with the usual rulemaking procedures, you will have a chance to comment on the proposed new rules when we publish the NPRM. In the preamble to any final rules, we will summarize and respond to the significant comments made on the NPRM. Why Are We Considering New Listings for Language and Speech Disorders? In our current listings, language and speech disorders are addressed in six separate listings in part A, and in 12 separate listings in part B, and these listings are spread across five different body systems (Special Senses and Speech; Multiple Body Systems; Neurological; Mental Disorders; Immune System). Some of these listings have narrow applicability, while others use different terminology to describe a language or speech impairment. Therefore, we are considering whether it would be better to establish a new body system that would (1) Describe disability at the listing level for individuals who have very serious language or speech problems, (2) provide a more focused, but also more comprehensive, means of evaluating E:\FR\FM\13APP1.SGM 13APP1

Agencies

[Federal Register Volume 70, Number 70 (Wednesday, April 13, 2005)]
[Proposed Rules]
[Pages 19345-19351]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-7380]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20917; Directorate Identifier 2004-NM-85-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-100, -200B, -200F, -
200C, -100B, -300, -100B SUD, -400, -400D, and -400F Series Airplanes;
and Model 747SR Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede two existing airworthiness
directives (AD) for certain Boeing transport category airplanes. One AD
currently requires doing certain inspections to detect cracks and
corrosion around the lower bearing of the actuator attach fittings of
the inboard and outboard flaps; repairing if necessary; and either
overhauling the fittings or replacing them, which when done on certain
actuator attach fittings ends the repetitive inspections. The other AD
currently requires certain other inspections to detect discrepancies of
the fittings of the flaps, and follow-on and corrective actions if
necessary, which ends the repetitive inspections of the first AD. For
certain airplanes, this proposed AD would require new inspections for
discrepancies of the attach fittings of the flaps, and follow-on and
corrective actions if necessary, which ends the repetitive inspections
of both existing ADs. For all airplanes, this proposed AD would require
repetitive overhaul/replacements of the fittings of both the inboard
and outboard flaps. This proposed AD is prompted by reports of cracks
of the attach fittings of the trailing edge flaps. We are proposing
this AD to prevent cracking and other damage of the actuator attach
fittings of the trailing edge flaps, which could result in abnormal
operation or retraction of a trailing edge flap, and possible loss of
controllability of the airplane.

DATES: We must receive comments on this proposed AD by May 31, 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 https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
You can get the service information identified in this proposed AD
from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207.
You may examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or 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.

FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6443; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track

[[Page 19346]]

each action and assign a corresponding directorate identifier. The DMS
AD docket number is in the form ``Docket No. FAA-2004-99999.'' The
Transport Airplane Directorate identifier is in the form ``Directorate
Identifier 2004-NM-999-AD.'' Each DMS AD docket also lists the
directorate identifier (``Old Docket Number'') as a cross-reference for
searching purposes.

Comments Invited

We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-20917;
Directorate Identifier 2004-NM-85-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of 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 may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications that affect you. You can get more information about
plain language at https://www.faa.gov/language and https://
www.plainlanguage.gov.

Examining the Docket

You may examine the AD docket 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 June 20, 2001, we issued AD 2001-13-12, amendment 39-12292 (66
FR 34526, June 29, 2001), for certain Boeing Model 747 series
airplanes. That AD requires repetitive inspections to detect cracks and
corrosion around the lower bearing of the actuator attach fittings of
the inboard and outboard flaps. That AD also requires repetitive
overhauls for certain actuator attach fittings or repetitive
replacement of the fittings with new fittings, as applicable, which
terminates the repetitive inspections. That AD also provides for
replacement of actuator attach fittings with improved fittings, which
terminates all requirements of that AD. That AD was prompted by reports
of cracks on the lower bearing journal of the inboard actuator attach
fittings of the outboard trailing edge flaps due to stress corrosion.
We issued that AD to detect and correct cracking on the actuator attach
fittings of the trailing edge flaps, which could result in abnormal
operation or retraction of a trailing edge flap, and consequent reduced
controllability of the airplane.
On April 14, 2003, we issued AD 2003-08-11, amendment 39-13124 (68
FR 19937, April 23, 2003), for all Boeing Model 747-100, -200B, -200F,
-200C, -100B, -300, -100B SUD, -400, -400D, and -400F series airplanes;
and Model 747SR series airplanes. That AD requires repetitive
inspections to detect discrepancies of the actuator attach fittings of
the inboard and outboard flaps, which are more comprehensive than those
required by AD 2001-13-12, and follow-on and corrective actions as
necessary. That AD was prompted by reports of three fractures of the
attach fittings of the trailing edge flap actuator. We issued that AD
to detect and correct cracking and other damage of the actuator attach
fittings of the trailing edge flaps, which could result in abnormal
operation or retraction of a trailing edge flap, and possible loss of
controllability of the airplane.
In the preamble of AD 2003-08-11, we indicated that the actions
required by that AD were considered ``interim action,'' and that
further rulemaking action was being considered to require repetitive
replacement of the fittings with new or overhauled fittings. We now
have determined that further rulemaking action is indeed necessary, and
this proposed AD follows from that determination.

Relevant Service Information

We have previously reviewed Boeing Alert Service Bulletin 747-
57A2316, dated December 19, 2002 (cited in AD 2003-08-11 as the
appropriate source of service information for the required actions).
The service bulletin describes procedures for repetitive inspections of
the attach fittings of the inboard and outboard flaps to detect
discrepancies (i.e., Part 1). The inboard fittings are to be inspected
using borescopic and detailed visual methods; and the outboard fittings
are to be inspected using borescopic, detailed visual, and ultrasonic
methods. The service bulletin also describes procedures for repetitive
detailed visual (inboard and outboard flaps) and ultrasonic (outboard
flap only) inspections with the attach fittings removed to detect
discrepancies (i.e., Part 2). Discrepancies include surface corrosion,
pitting, cracks, migrated or rotated bushings, and damaged or missing
cadmium plating. The service bulletin also describes procedures for
corrective and follow-on actions if necessary (i.e., Parts 3 through
5), which includes repetitive detailed visual inspections to detect
bushing migration and cracking and other damage of the actuator attach
fittings; repetitive application of corrosion-inhibiting compound; and
repetitive overhaul or replacement of any discrepant fitting with a new
or overhauled fitting; as applicable. Repetitive overhauls of the
attach fittings on the outboard and inboard flaps or repetitive
replacements of those attach fittings with new or overhauled fittings
(i.e., Part 5) ends the need for repetitive inspections.
The manufacturer advises that Boeing Alert Service Bulletin 747-
57A2316 replaces Boeing Alert Service Bulletin 747-57A2310 (cited as
the appropriate source of service information for the requirements of
AD 2001-13-12). We have determined that accomplishing the actions
specified in Boeing Service Bulletin 747-57A2316 will adequately
address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. Therefore, we are proposing this AD, which
would supersede ADs 2001-13-12 and 2003-08-11. This proposed AD would
continue to require the following actions specified in AD 2001-13-12:
Repetitive inspections to detect cracks and corrosion
around the lower bearing of the actuator attach fittings of

[[Page 19347]]

the inboard and outboard flaps, and repair if necessary; and
Repetitive overhauls of the actuator attach fittings on
the outboard flaps and a one-time overhaul of the fittings on the
inboard flaps, which ends the applicable repetitive inspections
described previously; or repetitive replacements of the fittings on the
inboard and outboard flaps with new fittings or a one-time replacement
of those fittings with improved fittings, which ends the repetitive
inspections described previously.
In addition, this proposed AD would continue to require the
following actions specified in AD 2003-08-11: Repetitive inspections to
detect discrepancies of the actuator attach fittings of the inboard and
outboard flaps (i.e., Part 1) and follow-on/corrective actions as
necessary (i.e, Parts 2 and 5). Accomplishing the initial inspections
(i.e., Part 1) would end the repetitive inspections around the lower
bearing of the fittings of the inboard and outboard flaps described
previously. This proposed AD would also require the actions specified
in Parts 2 through 5 of Boeing Alert Service Bulletin 747-57A2316
described previously, except as discussed under ``Difference Between
the Proposed AD and the Service Bulletin.'' Accomplishing the actions
in Part 2 of the service bulletin ends the inspections specified in
Part 1 of the service bulletin. Accomplishing the actions in Part 5 of
the service bulletin (i.e. repetitive overhauls or replacements of the
attaching fittings at intervals not to exceed 8 years) ends all
repetitive inspections for both inboard and outboard actuator attach
fittings over eight years old. The compliance times are as follows:
Part 1: 90 days (for inboard and outboard flaps);
Part 2: 9 months (for inboard flaps), 18 months (for
outboard flaps), and before further flight if any crack, corrosion, or
damaged cad plating is found on either the inboard or outboard flap;
Part 3: Repetitive intervals of 9 months (for inboard
flaps only);
Part 4: Repetitive intervals of 9 months (for outboard
flaps only); and
Part 5: Ranges from before the attach fitting is 8 years
old, or within 2 years, whichever occurs first, to 3 years depending on
the age of the outboard and inboard attach fittings. If any crack,
corrosion, or damaged cad plating is found on either the inboard or
outboard flap, the compliance time is before further flight.

Difference Between the Proposed AD and the Service Bulletin

Boeing Alert Service Bulletin 747-57A2316 refers to ``detailed
visual inspection'' for discrepancies of the actuator attach fittings
of the inboard and outboard flaps. We have determined that the
procedures in the service bulletin should be described as a ``detailed
inspection.'' Note 1 has been included in this proposed AD to define
this type of inspection.

Change to Existing ADs

This proposed AD would retain all requirements of ADs 2001-13-12
and 2003-08-11. Since those ADs were 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 two tables:

Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2001-13-12 this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (g)
paragraph (b)............................. paragraph (h)
paragraph (c)............................. paragraph (i)
paragraph (d)............................. paragraph (j)
paragraph (e)............................. paragraph (k)
paragraph (f)............................. paragraph (l)
------------------------------------------------------------------------

------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2003-08-11 this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (m)
paragraph (b)............................. paragraph (n)
paragraph (c)............................. paragraph (o)
paragraph (d)............................. paragraph (p)
------------------------------------------------------------------------

We also have changed all references to a ``detailed visual
inspection'' in the existing ADs to ``detailed inspection'' in this
action. In addition, we have added a new requirement that, as of the
effective date of this AD, the repetitive overhauls and replacements in
paragraphs (j)(1) and (k)(1) of this proposed AD (paragraphs (d) and
(e)(1) of AD 2001-13-12), respectively, must be done in accordance with
Part 5 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2316, dated December 19, 2002, at intervals not to
exceed 8 years. The repetitive intervals for those repetitive
requirements in AD 2001-13-12 are 8 years or 8,000 flight cycles,
whichever occurs first. Because corrosion is time dependant rather than
flight-cycle dependant, we determined that the intervals for the
repetitive overhauls and replacements should be based on time only. We
also determined that operators should accomplish those actions in
accordance with the latest service bulletin.

Costs of Compliance

This proposed AD would affect about 1,000 Model 747-100, -200B, -
200F, -200C, -100B, -300, -100B SUD, -400, -400D, and -400F series
airplanes; and Model 747SR series airplanes worldwide. There are about
181 airplanes on the U.S. registry. The average labor rate is $65 per
hour. The following two tables provide the estimated costs for U.S.
operators to comply with this proposed AD.

Table 1.--Estimated Costs
----------------------------------------------------------------------------------------------------------------
Work
Action hours Parts Cost per airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD 2001- 2 None................. $130, per inspection $23,530, per
13-12). cycle. inspection cycle.
Inspections specified in Part 1 of 2 None................. $130 per inspection $23,530 per
the Accomplishment Instruction cycle. inspection cycle.
(AI) of the referenced service
bulletin (required by AD 2003-08-
11).
Inspections specified in Part 2 of 5 None................. $325 per inspection $58,825 per
the AI of the referenced service cycle. inspection cycle.
bulletin (new proposed actions).
----------------------------------------------------------------------------------------------------------------

[[Page 19348]]

Table 2.--Estimated Costs
----------------------------------------------------------------------------------------------------------------
Work
Action hours Parts Cost per airplane
----------------------------------------------------------------------------------------------------------------
Overhaul(s) as an alternative to the 37 None.......................... $2,405.
replacement.
Replacement(s) as an alternative to 4 $6,623 (for the four attach $6,883 (for the four attach
the overhaul. fittings on the outboard fittings on the outboard
flaps) and $7,566 (for the flaps) and $7,826 (for the
four attach fittings on the four attach fittings on the
inboard flaps). inboard flaps), per
replacement 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:

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 amendments 39-12292 (66
FR 34526, June 29, 2001) and 39-13124 (68 FR 19937, April 23, 2003) and
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2005-20917; Directorate Identifier 2004-NM-
85-AD.

Comments Due Date

(a) The Federal Aviation Administration must receive comments on
this airworthiness directive (AD) action by May 31, 2005.

Affected ADs

(b) This AD supersedes AD 2001-13-12, amendment 39-12292; and AD
2003-08-11, amendment 39-13124.
Applicability: (c) This AD applies to all Boeing Model 747-100,
-200B, -200F, -200C, -100B, -300, -100B SUD, -400, -400D, and -400F
series airplanes; and Model 747SR series airplanes; certificated in
any category.

Unsafe Condition

(d) This AD was prompted by reports of cracks of the attach
fittings of the trailing edge flaps. We are issuing this AD to
prevent cracking and other damage of the actuator attach fittings of
the trailing edge flaps, which could result in abnormal operation or
retraction of a trailing edge flap, and possible loss of
controllability of the airplane.
Compliance: (e) You are responsible for having the actions
required by this AD performed within the compliance times specified,
unless the actions have already been done.

Requirements of AD 2001-13-12

Affected Airplanes

(f) For Boeing Model 747 series airplanes, as listed in Boeing
Service Bulletin 747-57A2310, Revision 2, dated February 22, 2001,
do the actions required by paragraphs (g) through (l) of this AD, as
applicable.

Actuator Attach Fittings That Have Not Been Overhauled or Replaced

(g) For actuator attach fittings on the outboard flaps that have
not been overhauled in accordance with revisions of Boeing 747
Overhaul Manual (OHM) 57-52-55 dated prior to June 1, 1999, or
replaced with a new fitting, prior to August 3, 2001 (the effective
date of AD 2001-13-12); and for actuator attach fittings on the
inboard flap actuators that have not been overhauled in accordance
with revisions of OHM 57-52-35, dated prior to June 1, 1999, or
replaced with a new fitting, prior to August 3, 2001: Accomplish the
actions in paragraph (i), (j), or (k) of this AD at the later of the
times specified in paragraphs (g)(1) and (g)(2) of this AD.
(1) Prior to the accumulation of 8 years since date of
manufacture or 8,000 total flight cycles, whichever occurs first.
(2) Within 6 months after August 3, 2001.

Actuator Attach Fittings That Have Been Overhauled or Replaced

(h) For actuator attach fittings on the outboard flaps that have
been overhauled in accordance with revisions of OHM 57-52-55 dated
prior to June 1, 1999, or replaced with a new fitting, prior to
August 3, 2001; and for actuator attach fittings on the inboard flap
actuators that have been overhauled in accordance with revisions of
OHM 57-52-35 dated prior to June 1, 1999, or replaced with a new
fitting, prior to August 3, 2001:
Accomplish the actions in paragraph (i), (j), or (k) of this AD at
the later of the times specified in paragraphs (h)(1) and (h)(2) of
this AD.
(1) Within 8 years or 8,000 total flight cycles after the attach
fitting was overhauled or replaced, whichever occurs first.
(2) Within 6 months after August 3, 2001.

Inspections and Corrective Action

(i) Perform a detailed inspection to detect corrosion around the
lower bearing journal on the actuator attach fittings on the inboard
and outboard flaps, and perform an ultrasonic inspection to detect
cracks around the lower bearing journal of the actuator attach
fittings on the outboard flaps, in accordance with Boeing Service
Bulletin 747-57A2310, Revision 1, dated November

[[Page 19349]]

23, 1999; or Revision 2, dated February 22, 2001.

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.''

Note 2: Inspections, overhauls, and replacements accomplished in
accordance with Boeing Alert Service Bulletin 747-57A2310, dated
June 17, 1999, are acceptable for compliance with the requirements
of paragraph (i) of this AD.

(1) If no corrosion or cracks are detected, repeat the
inspections required by paragraph (i) of this AD at intervals not to
exceed 18 months. Within 5 years after the initial inspections
required by paragraph (i) of this AD, accomplish the actions
specified in paragraph (j) or (k) of this AD.
(2) If any corrosion is detected, prior to further flight,
remove the corrosion by accomplishing the actions of either
paragraph (i)(2)(i) or (i)(2)(ii) of this AD.
(i) If corrosion is within the limits of the Boeing 747 OHM:
Prior to further flight, accomplish the actions specified in
paragraph (j) or (k) of this AD.
(ii) If corrosion is not within the limits of the Boeing 747
OHM: Prior to further flight, accomplish the actions specified in
paragraph (k) or (l) of this AD.
(3) If any crack is detected: Prior to further flight,
accomplish the actions specified in paragraph (k) or (l) of this AD.

Overhaul

(j) Do the actions as specified in paragraphs (j)(1) and (j)(2)
of this AD in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-57A2310, Revision 1, dated November 23,
1999; or Revision 2, dated February 22, 2001.
(1) Overhaul the actuator attach fittings on the outboard flaps.
Repeat the overhaul of actuators on the outboard flaps as specified
in Part 2 of the Work Instructions of the service bulletin
thereafter at intervals not to exceed 8 years or 8,000 flight
cycles, whichever occurs first. As of the effective date of this AD,
the repetitive overhauls must be done in accordance with Part 5 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2316, dated December 19, 2002, at intervals not to exceed 8
years since last overhaul. Accomplishment of the overhaul of the
actuator attach fittings on the outboard flaps constitutes
terminating action for the repetitive inspection requirements of
paragraph (i)(1) of this AD for outboard flaps.
(2) Overhaul the actuator attach fittings on the inboard flaps.
Accomplishment of the overhaul of the actuator attach fittings on
the inboard flaps constitutes terminating action for the
requirements of paragraphs (g) through (l) of this AD for the
actuator attach fittings on the inboard flaps.

Replacement

(k) Replace the actuator attach fittings on the inboard and
outboard flaps in accordance with paragraph (k)(1) or (k)(2) of this
AD.
(1) Replace the actuator attach fittings on the inboard and
outboard flaps with new attach fittings in accordance with ``Part
3--Replacement'' of Boeing Service Bulletin 747-57A2310, Revision 1,
dated November 23, 1999; or Revision 2, dated February 22, 2001.
Accomplishment of this replacement constitutes terminating action
for the repetitive inspections required by paragraph (i) of this AD
for the replaced fitting. Within 8 years or 8,000 flight cycles
following accomplishment of the replacement, whichever occurs first,
repeat this replacement or accomplish the overhaul specified in
paragraph (j) of this AD. As of the effective date of this AD, the
repetitive replacements must be done in accordance with Part 5 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2316, dated December 19, 2002, at intervals not to exceed 8
years since last replacement.
(2) Replace the actuator attach fittings on the inboard and
outboard flaps with improved attach fittings in accordance with
``Part 4--Terminating Action'' of Boeing Service Bulletin 747-
57A2310, Revision 2, dated February 22, 2001. If accomplished, this
replacement with improved fittings terminates the requirements of
paragraphs (g) through (l) of this AD for the replaced fitting.

Note 3: Replacement of the actuator attach fittings on the
inboard flaps with fittings that have been overhauled before the
effective date of this AD, in accordance with Boeing OHM 57-52-35,
Temporary Revision 57-8, dated June 10, 1999; Temporary Revision 57-
10, dated May 8, 2000; or Full Revision 57-10, dated July 1, 2000;
constitutes terminating action for the requirements of paragraphs
(g) through (l) of this AD for the actuator attach fittings on the
inboard flaps.

Repair

(l) During any inspection done in accordance with paragraph (i)
of this AD, if corrosion is found that is outside the limits
specified in the Boeing 747 OHM, or if any crack is detected: In
lieu of replacement of the actuator attach fittings in accordance
with paragraph (k) of this AD, repair the actuator attach fittings
on the inboard and outboard flaps in accordance with a method
approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA; or per data meeting the type certification basis of the
airplane approved by a Boeing Company Designated Engineering
Representative who has been authorized by the Manager, Seattle ACO,
to make such findings. For a repair method to be approved by the
Manager, Seattle ACO, as required by this paragraph, the Manager's
approval letter must specifically reference this AD.

Requirements of AD 2003-08-11

Inspection: Inboard Flap Attach Fittings

(m) Perform borescopic and detailed inspections to detect
discrepancies of the inboard flap attach fittings, in accordance
with Part 1 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-57A2316, dated December 19, 2002. Discrepancies
include corrosion, pitting, and damaged or missing cadmium plating.
Do the inspection at the applicable time specified in paragraph
(m)(1) or (m)(2) of this AD.
(1) If the age of the fittings can be determined: Inspect within
14 years since the fittings were new or last overhauled, or within
90 days after May 8, 2003 (the effective date of AD 2003-08-11),
whichever occurs later.
(2) If the age of the fittings cannot be determined: Inspect
within 90 days after May 8, 2003.

Note 4: The exceptions specified in flag note 4 of Figure 1 of
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002,
apply to the requirements of paragraphs (m) and (n) of this AD.

Inspection: Outboard Flap Attach Fittings

(n) Perform borescopic, detailed, and ultrasonic inspections to
detect discrepancies of the outboard flap attach fittings, in
accordance with Part 1 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2316, dated December 19, 2002.
Discrepancies include surface corrosion, pitting, damaged or missing
cadmium plating, and cracks. Do the inspection at the applicable
time specified in paragraph (n)(1) or (n)(2) of this AD.
(1) If the age of the fittings can be determined: Inspect within
8 years since the fittings were new or last overhauled, or within 90
days May 8, 2003, whichever occurs later.
(2) If the age of the fittings cannot be determined: Inspect
within 90 days after May 8, 2003.

Follow-on Actions: No Discrepancies Found

(o) If no discrepancy is found during any inspection required by
paragraph (m) or (n) of this AD: Do the actions specified by either
paragraph (o)(1) or paragraph (o)(2) of this AD.
(1) Repeat the applicable inspections specified in paragraphs
(m) and (n) of this AD at intervals not to exceed 9 months until the
actions specified in paragraph (o)(2) of this AD have been
accomplished.
(2) Perform a detailed inspection of the fitting to detect
cracks, corrosion, damaged cadmium plating, or bushing migration, in
accordance with and at the time specified in Part 2 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2316, dated December 19, 2002. Do the follow-on actions in
accordance with Parts 3, 4, and 5 of the Accomplishment Instructions
of the service bulletin at the times specified in Figure 1 of the
service bulletin, as applicable. Accomplishment of these actions
terminates the initial and repetitive inspection requirements of
paragraphs (m), (n), and (o)(1) of this AD.

Note 5: The exceptions specified in flag note 2 of Figure 1 of
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002,
apply to those requirements of paragraphs (o)(2) and (p) of this AD
that are specified in Part 2 of the service bulletin.

[[Page 19350]]

Corrective/Follow-on Actions: Discrepancies Found

(p) If any discrepancy is found during any inspection required
by paragraph (m), (n), or (o) of this AD: Perform applicable
corrective and follow-on actions at the time specified and in
accordance with Figure 1 of Boeing Alert Service Bulletin 747-
57A2316, dated December 19, 2002. Before further flight: Replace any
discrepant fitting in accordance with Part 5 of the Accomplishment
Instructions of the service bulletin, and accomplish the follow-on
actions for the other fittings common to that flap in accordance
with Part 2 of the Accomplishment Instructions of the service
bulletin. Replacement of a fitting terminates the initial and
repetitive inspections--specified in paragraphs (m), (n), and (o) of
this AD--for that fitting only.

Terminating Action for Certain Requirements

(q) Accomplishment of the actions required by paragraphs (m) and
(n) of this AD ends the requirements of paragraphs (g) through (k)
of this AD, except for the repetitive overhauls and repetitive
replacements required by paragraphs (j)(1) and (k)(1) of this AD,
respectively.

New Actions Required by This AD

Inspections: Attach Fittings of the Inboard and Outboard Flaps

(r) For airplanes on which the repetitive borescopic, detailed,
or ultrasonic (as applicable) inspections required by paragraphs
(m), (n), or (o)(1) of this AD are being done as of the effective
date of this AD: Inspect as specified in Table 1 of this AD.
Accomplishing these actions ends the initial and repetitive
inspections required by paragraphs (m), (n), and (o)(1) of this AD.

Table 1.--Inspections of Attach Fittings
------------------------------------------------------------------------
Requirements Description
------------------------------------------------------------------------
(1) Compliance time.................. Except as provided by paragraph
(u) of this AD, at the
applicable time specified in
Figure 1 of Boeing Alert Service
Bulletin 747-57A2316, dated
December 19, 2002.
(2) Area to inspect.................. The attach fittings of the
inboard and outboard flaps.
(3) Type of inspection............... Detailed inspection (inboard and
outboard flaps) and ultrasonic
inspection (outboard flaps
only).
(4) Discrepancies to detect.......... Surface corrosion, pitting,
cracks, migrated or rotated
bushings, and damaged or missing
cadmium plating.
(5) In accordance with............... Part 2 of the Work Instructions
of Boeing Alert Service Bulletin
747-57A2316, dated December 19,
2002.
------------------------------------------------------------------------

Follow-on Actions: No Discrepancies Detected

(s) If no discrepancy is detected during any inspection required
by paragraph (r) of this AD: Do the follow-on actions in accordance
with Parts 3, 4, and 5, as applicable, of the Work Instructions of
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002,
at the applicable times specified in Figure 1 of the service
bulletin, except as provided by paragraph (u) of this AD.

Overhaul/Replacement and Follow-on/Corrective Actions: Discrepancies
Detected

(t) If any discrepancy is detected during any inspection
required by paragraph (r) of this AD: Do the actions specified in
Table 2 of this AD at the applicable times specified in Figures 1
and 2 of the service bulletin, except as provided by paragraph (v)
of this AD.

Table 2.--Discrepancies Found
------------------------------------------------------------------------
In accordance with Boeing Alert
Requirements Service Bulletin 747-57A2316,
dated December 19, 2002--
------------------------------------------------------------------------
(1) Overhaul or replace discrepant Part 5 of Work Instructions.
fitting with new fitting.
(2) Do the follow-on and corrective Parts 2 and 5 of Work
actions for the other fitting common Instructions, as applicable.
to that flap, except as specified in
flag note 2 in Figure 1 of the service
bulletin.
------------------------------------------------------------------------

Compliance Time Requirements

(u) For the requirements of paragraph (r) of this AD: Where
Figure 1 of Boeing Alert Service Bulletin 747-57A2316, dated
December 19, 2002, states a compliance time ``after the original
issue date of the service bulletin,'' this AD requires compliance
within the applicable compliance time after the effective date of
this AD.
(v) For the requirements of paragraph (s) of this AD: Where
Figure 1 of Boeing Alert Service Bulletin 747-57A2316, dated
December 19, 2002, specifies to repeat the overhaul or replacement
``every 8 years,'' this AD requires compliance at intervals not to
exceed 8 years.

Repetitive Overhaul or Replacement

(w) Except as provided in paragraph (x) of this AD, at the
applicable time specified in paragraph (w)(1) or (w)(2) of this AD,
overhaul the attach fittings on the outboard and inboard flaps or
replace the attach fittings with new or overhauled fittings, in
accordance with Part 5 of the Work Instructions of Boeing Alert
Service Bulletin 747-57A2316, dated December 19, 2002. Repeat the
overhaul or replacement thereafter at intervals not to exceed 8
years.
(1) If the age of the fittings can be determined: Overhaul or
replace within 8 years since the fittings were new or last
overhauled, or within 2 years after the effective date of this AD,
whichever occurs later.
(2) If the age of the fittings cannot be determined: Assume that
the fittings are more than 14 years old, and overhaul or replace
within 2 years after the effective date of this AD.
(x) Accomplishing the repetitive overhauls required by paragraph
(j)(1) or repetitive replacements required by paragraph (k)(1) of
this AD is acceptable for compliance with the requirements of
paragraph (w) of this AD.

Alternative Methods of Compliance (AMOCs)

(y)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) 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.
(3) AMOCs approved previously in accordance with AD 2001-13-12
are approved as AMOCs with the actions required by paragraphs (g)
through (l) of this AD, as applicable. However, AMOCs approved
previously are not considered

[[Page 19351]]

terminating action for the repetitive overhauls or replacements
requirements of this AD.
(4) AMOCs approved previously in accordance with AD 2003-08-11
are approved as AMOCs with the actions required by paragraphs (m)
through (p) of this AD, as applicable.

Issued in Renton, Washington, on April 6, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-7380 Filed 4-12-05; 8:45 am]
BILLING CODE 4910-13-P

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