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 Department of Transportation Federal Aviation Administration 14 CFR Part 39
[Docket No. FAA-2014-0431; Directorate Identifier 2013-NM-041-AD; Amendment 39-18003; AD 2014-21-09]
RIN 2120-AA64
 AGENCY: Federal Aviation Administration (FAA), DOT.
 ACTION: Final rule.
 SUMMARY: We are superseding Airworthiness Directive (AD) 2005-14-07 for certain The Boeing Company Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes. AD 2005-14-07 required repetitive inspections of the carriage attach fittings on the inboard and outboard foreflaps of each wing for cracking and other discrepancies, and corrective actions if necessary. This new AD requires reducing certain repetitive inspection intervals for the inboard and outboard 
                        ( print page 64307)
                        carriage attach fittings for the outboard foreflaps, requires previously optional terminating actions which install improved outboard foreflap carriage attach fittings, and adds new initial and repetitive inspections of those fittings and corrective actions if necessary. This AD was prompted by a report of broken inboard and outboard carriage attach fittings of the outboard foreflaps found during an inspection. We are issuing this AD to detect and correct fatigue cracking of the attach fittings of the foreflap carriage of the wings, which could result in partial or complete loss of the foreflap and consequent loss of controllability of the airplane.
 DATES: This AD is effective December 3, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 3, 2014. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of August 15, 2005 (70 FR 39647, July 11, 2005).
 ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet 
                        *https://www.myboeingfleet.com.*
                         You may view this referenced service information at the FAA, Transport Aircraft Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket You may examine the AD docket on the Internet at 
                    *http://www.regulations.gov*
                     by searching for and locating Docket No. FAA-2014-0431; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
 FOR FURTHER INFORMATION CONTACT: Chandraduth Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; email 
                        *chandraduth.ramdoss@faa.gov.*


SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005). AD 2005-14-07 applied to certain The Boeing Company Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes. The NPRM published in the 
                    **Federal Register**
                     on July 9, 2014 (79 FR 38801). The NPRM was prompted by a report of broken inboard and outboard carriage attach fittings of the outboard foreflaps found during an inspection required by AD 2005-14-07. The airplane had 47,125 flight cycles. Boeing stated that the metallurgical analysis determined that the cause of the broken fittings is a suspected static overload condition. The NPRM proposed to continue to require repetitive inspections of the carriage attach fittings on the inboard and outboard foreflaps of each wing for cracking and other discrepancies, and corrective actions if necessary. The NPRM also proposed to require reducing certain repetitive inspection intervals for the inboard and outboard carriage attach fittings for the outboard foreflaps, requiring previously optional terminating actions which install improved outboard foreflap carriage attach fittings, and adding new initial and repetitive inspections of those fittings and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking of the attach fittings of the foreflap carriage of the wings, which could result in partial or complete loss of the foreflap and consequent loss of controllability of the airplane. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comment received. Boeing supported the NPRM (79 FR 38801, July 9, 2014). Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: Are consistent with the intent that was proposed in the NPRM (79 FR 38801, July 9, 2014) for correcting the unsafe condition; and
                Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 38801, July 9, 2014). Costs of Compliance We estimate that this AD affects 98 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Retained Estimated Costs
Retained action
Labor cost
Parts cost
Cost per product
Cost on U.S. 
                             operatorsInspections of the carriage attach fittings for all airplanes [retained actions from AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005)]
4 work-hours  × $85 per hour = $340
None
$340 per airplane, per inspection cycle
$33,320, per inspection cycle.Installation of guide blocks for certain airplanes [retained actions from AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005)]
32 work-hours × $85 per hour = $2,720
$0
$2,720 per airplane
Up to $266,560.Inspection of foreflap airload roller travel for certain airplanes [retained actions from AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005)]
4 work-hours × $85 per hour = $340
None
$340 per airplane
Up to $33,320.( print page 64308)Modification of the inboard jackscrews on the outboard flap for certain airplanes [retained actions from AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005)]
4 work-hours × $85 per hour = $340
$0
$340 per airplane
Up to $33,320.Inspection of the entire track and of the track rib faces for certain airplanes [retained actions from AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005)]
12 work-hours × $85 per hour = $1,020
None
$1,020 per airplane
Up to $99,960.
 Estimated Costs for New Actions
Retained action
Labor cost
Parts cost
Cost per product
Cost on U.S. 
                             operatorsInspection and functional check of outboard foreflap installation for all airplanes [new action]
3 work-hours × $85 per hour = $255 per inspection cycle
None
$255, per inspection cycle
$24,990, per inspection cycle.Replacement of carriage attach fitting on outboard foreflap for certain airplanes [new action]
2 work-hours × $85 per hour = $170
$18,000
$18,170 per airplane
Up to $1,780,660.
 We estimate the following costs to do any necessary replacements that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these replacements: On-Condition Costs
Action
Labor cost
Parts cost
Cost per productReplacement of sequence carriage slider or sidewall rubstrips
2 work-hours × $85 per hour = $170
Up to $175
Up to $345.
 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD: (1) Is not a “significant regulatory action” under Executive Order 12866, (2) Is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) 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. List of Subjects in 14 CFR Part 39 Air transportation
Aircraft
Aviation safety
Incorporation by reference
Safety
 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES
 1.The authority citation for part 39 continues to read as follows: Authority:
                        49 U.S.C. 106(g), 40113, 44701. § 39.13
 2.The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2005-14-07, Amendment 39-14184 ( 70 FR 39647, July 11, 2005), and adding the following new AD: **2014-21-09 The Boeing Company:**
                             Amendment 39-18003; Docket No. FAA-2014-0431; Directorate Identifier 2013-NM-041-AD. (a) Effective Date This AD is effective December 3, 2014. (b) Affected ADs This AD replaces AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005). (c) Applicability This AD applies to Boeing Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes, certificated in any category, as listed in Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002.
                            ( print page 64309) (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by a report of broken carriage attach fittings of the inboard and outboard foreflaps found during an inspection and an additional report of broken inboard and outboard carriage attach fittings of the outboard foreflaps found during an inspection. We are issuing this AD to detect and correct fatigue cracking of the attach fittings of the foreflap carriage of the wings, which could result in partial or complete loss of the foreflap and consequent loss of controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspections This paragraph restates the requirements of paragraph (f) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with revised service information and a new compliance time. Except as provided by paragraph (l) of this AD: Within 1,000 flight cycles after August 15, 2005 (the effective date of AD 2005-14-07) or within 6 months after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 1,000 flight cycles, except as required by paragraph (m) of this AD (for outboard foreflaps), inspect as specified in paragraphs (g)(1) and (g)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; or Revision 4, dated September 26, 2012. As of the effective date of this AD, use only Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. Accomplishing the actions of paragraph (m) or (o) of this AD terminates the inspections required by this paragraph for outboard foreflaps only. (1) A detailed inspection to detect cracks and surface deviations on all edges, surfaces, and lug attachment fastener holes on the two carriage attach fittings on the inboard and outboard foreflaps of each wing. (2) A high frequency eddy current (HFEC) inspection to detect cracks at the lug attachment fastener holes on the two carriage attach fittings on the inboard and outboard foreflaps of each wing. (h) Retained Replacement This paragraph restates the requirements of paragraph (g) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with revised service information. If any crack is detected or if any surface deviation beyond the limits specified in Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; or Revision 4, dated September 26, 2012; is detected during any inspection required by paragraph (g) or (m) of this AD, before further flight, replace the carriage attach fitting with a new, improved fitting or a new fitting having the same part number as the existing fitting, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; or Revision 4, dated September 26, 2012. As of the effective date of this AD, use only Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. (i) Retained Measurement and Associated Corrective Action(s) (1) This paragraph restates the requirements of paragraph (h) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with revised service information. Within 3,500 flight cycles after August 15, 2005 (the effective date of AD 2005-14-07), inspect for interference between the carriage attach fitting and the carriage lug fitting, and do other related investigative actions by accomplishing all the actions specified in paragraph 3.C. and Figure 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; or paragraph 3.B.3 and Figure 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. Do the actions in accordance with Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; or Revision 4, dated September 26, 2012. As of the effective date of this AD, use only Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. (2) Paragraphs (i)(2)(i) and (i)(2)(ii) of this AD restate the requirements of paragraph (i) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with revised service information. (i) If any discrepancy is found during any action required by paragraph (i)(1) of this AD, before further flight, accomplish applicable corrective action(s) (e.g., adding a shim or reworking the carriage attachment lug assembly), in accordance with paragraph 3.C. and Figure 2 or 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; or paragraph 3.B.3. and Figure 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012; except as required by paragraph (i)(2)(ii) of this AD. As of the effective date of this AD, use only Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. (ii) Where Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; or Revision 4, dated September 26, 2012; specify to contact the manufacturer if rework of the improved fitting is required: Before further flight, rework in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), or Los Angeles ACO, FAA; or in accordance with data meeting the type certification basis of the airplane approved by an Authorized Representative (AR) for the Boeing Delegation Option Authorization (DOA) Organization who has been authorized by the FAA to make such findings; or using a method approved in accordance with the procedures specified in paragraph (s) of this AD. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically reference this AD. As of the effective date of this AD, any new repair approval must be done using a method approved in accordance with the procedures specified in paragraph (s) of this AD. (j) Retained Concurrent Requirements (1) This paragraph restates the requirements of paragraph (j) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with new paragraph reference. For Model 727 airplanes listed in Boeing 727 Service Bulletin 57-59, Revision 1, dated September 27, 1965: Before or at the same time with the requirements of paragraph (i) or (o) of this AD, install guide blocks and bushings in the midflap ribs in accordance with the Accomplishment Instructions of Boeing 727 Service Bulletin 57-59, Revision 1, dated September 27, 1965. (2) This paragraph restates the requirements of paragraph (k) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with new paragraph reference. For Model 727 airplanes listed in Boeing Service Bulletin 727-27-133, Revision 1, dated May 9, 1972: Before or at the same time with the requirements of paragraph (i) or (o) of this AD, do the actions specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD, as applicable. (i) For Groups I and II airplanes identified in Boeing Service Bulletin 727-27-133, Revision 1, dated May 9, 1972: Do a one-time inspection of the airload support roller for travel on the foreflap track, in accordance with Part I of the Accomplishment Instructions of Boeing Service Bulletin 727-27-133, Revision 1, dated May 9, 1972. (A) If the airload support roller travels within the limits specified in Boeing Service Bulletin 727-27-133, Revision 1, dated May 9, 1972, modify the control drum of the inboard flap and inboard jackscrews of the outboard flap, in accordance with Part II of the Accomplishment Instructions of Boeing Service Bulletin 727-27-133, Revision 1, dated May 9, 1972. (B) If the airload support roller travels beyond the limits specified in Boeing Service Bulletin 727-27-133, Revision 1, dated May 9, 1972, repair in accordance with a method approved by the Manager, Seattle ACO, or Los Angeles ACO, FAA; or in accordance with data meeting the type certification basis of the airplane approved by an AR for the Boeing DOA Organization who has been authorized by the FAA to make such findings; or using a method approved in accordance with the procedures specified in paragraph (s) of this AD. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically reference this AD. As of the effective date of this AD, any new repair approval must be done using a method approved in accordance with the procedures specified in paragraph (s) of this AD. (ii) For Group III airplanes identified in Boeing Service Bulletin 727-27-133, Revision 1, dated May 9, 1972: Modify the inboard jackscrews of the outboard flap (i.e., replacing the down stop at the inboard jackscrews of the outboard flap) in accordance with Part II of the 
                            ( print page 64310)
                            Accomplishment Instructions of Boeing Service Bulletin 727-27-133, Revision 1, dated May 9, 1972. (3) This paragraph restates the requirements of paragraph (l) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with new paragraph reference. For Model 727 airplanes listed in Boeing 727 Service Bulletin 57-72, dated September 21, 1966: Before or at the same time with the requirements of paragraph (i) or (o) of this AD, do the actions specified in paragraphs (j)(3)(i) through (j)(3)(iv) of this AD. (i) Chamfer the upper and lower flanges at the aft end of the foreflap tracks in accordance with the Accomplishment Instructions of Boeing 727 Service Bulletin 57-72, dated September 21, 1966. (ii) Do a standard magnetic particle inspection of the entire foreflap tracks for cracks in accordance with the Accomplishment Instructions of Boeing 727 Service Bulletin 57-72, dated September 21, 1966. If any crack is detected, before further flight, repair in accordance with a method approved by the Manager, Seattle ACO, or Los Angeles ACO, FAA; or in accordance with data meeting the type certification basis of the airplane approved by an AR for the Boeing DOA Organization who has been authorized by the FAA to make such findings; or using a method approved in accordance with the procedures specified in paragraph (s) of this AD. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically reference this AD. As of the effective date of this AD, any new repair approval must be done using a method approved in accordance with the procedures specified in paragraph (s) of this AD. (iii) Do a general visual inspection of the track rib faces at the front and rear spars to verify if the opening in the spars is flush with or clear of the plane of the rib faces, in accordance with the Accomplishment Instructions of Boeing 727 Service Bulletin 57-72, dated September 21, 1966. If the opening is not flush or clear with the plane, before further flight, rework the spar opening in accordance with the Accomplishment Instructions of Boeing 727 Service Bulletin 57-72, dated September 21, 1966. (iv) Do a general visual inspection of the head or shank of bolts by securing the foreflap links to the foreflap tracks to verify if they protrude beyond the edge of the track flange in accordance with the Accomplishment Instructions of Boeing 727 Service Bulletin 57-72, dated September 21, 1966. If the head or shank of the bolts protrude beyond the edge of the track flange, before further flight, rework in accordance with the Accomplishment Instructions of Boeing 727 Service Bulletin 57-72, dated September 21, 1966. (v) For the purposes of this AD, a general visual inspection is defined as: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.” (4) This paragraph restates the requirements of paragraph (m) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with a new paragraph identifier. For airplanes other than those identified in the service information specified in paragraphs (j)(1) through (j)(3) of this AD: Before or at the same time with the requirements of paragraph (i) or (o) of this AD, do an inspection to verify if any of the parts listed in the “Spares Affected” paragraph of each service information referenced in paragraphs (j)(1) through (j)(3) of this AD are installed on the airplane. If any part identified in that paragraph is found installed, before further flight, do the applicable corrective and investigative action(s) specified in paragraphs (j)(1) through (j)(3) of this AD. (k) Retained Optional Terminating Actions This paragraph restates the requirements of paragraph (n) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with no changes. Replacement of the two carriage attach fittings on the inboard and outboard foreflaps of each wing with new, improved fittings, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; and accomplishment of the actions specified in paragraphs (j)(1) through (j)(4) of this AD, as applicable, before or concurrently with the replacement; constitutes terminating action for paragraphs (g) through (j) of this AD and paragraph (l) of this AD for those replaced fittings on the outboard and inboard foreflaps. (l) Retained Optional Deferral of Inspection This paragraph restates the optional deferral of paragraph (o) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with no changes. Replacement of the two carriage attach fittings on the inboard and outboard foreflaps of each wing with new fittings having the same part number as the existing fittings, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; and accomplishment of the actions specified in paragraphs (j)(1) through (j)(4) of this AD, as applicable, before or concurrently with the replacement; defers the next inspection required by paragraph (g) of this AD for 10,000 flight cycles after the replacement. Thereafter, repeat the inspections required by paragraph (g) of this AD at intervals not to exceed 1,000 flight cycles, except as required by paragraph (m) of this AD. (m) New Detailed and HFEC Inspections of Outboard Foreflaps, With Reduced Repetitive Intervals Within 1,000 flight cycles after the most recent accomplishment of the inspections required by paragraph (g) of this AD, do a detailed inspection to detect cracks and surface deviations on all edges, surfaces, and lug attachment fastener holes, and a HFEC inspection to detect cracks at the lug attachment fastener holes, on the two carriage attach fittings on the outboard foreflaps of each wing, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012, and do all applicable corrective actions required by paragraph (h) of this AD. Repeat the inspections thereafter at intervals not to exceed 200 flight cycles until the requirements of paragraph (o) of this AD is accomplished. Accomplishing the requirements of this paragraph terminates the requirements of paragraph (g) of this AD for the outboard foreflaps only. (n) New Inspection and Check of Outboard Foreflap Installation and Corrective Action Within 200 flight cycles or 6 months after the effective date of this AD, whichever occurs first, do a general visual inspection and function check for damage and incorrect operation of the outboard foreflap installations, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. Do the applicable corrective actions before further flight. Thereafter, repeat the inspection and check at intervals not to exceed 500 flight cycles. (o) New Replacement of Previously Un-Replaced (or “Original Configuration”) Carriage Attach Fittings on the Outboard Foreflap For airplanes on which any production carriage attach fitting is still installed on the outboard foreflap: Within 3,000 flight cycles or 3 years after the effective date of this AD, whichever occurs first, replace all production carriage attach fittings with new, improved carriage attach fittings, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012, and do all applicable concurrent actions required by paragraph (k) of this AD. Accomplishing the requirements of this paragraph terminates the requirements of paragraphs (g) and (m) of this AD for outboard foreflaps only. (p) New Inspection, Corrective Action and Replacement of Fittings Replaced in Accordance With Paragraph (l) of This AD For airplanes on which a new carriage attach fitting with the original part number on the outboard foreflap was installed in accordance with paragraph (l) of this AD: Do the actions specified in paragraphs (p)(1) and (p)(2) of this AD. (1) Within 1,000 flight cycles after the effective date of this AD, do a detailed inspection for cracks and surface deviation on all edges surfaces, and lug attachment fastener holes, and a HFEC inspection for cracks at the lug attachment fastener holes, on the carriage attach fittings for the outboard foreflaps, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. Repeat the inspection at intervals not to exceed 200 
                            ( print page 64311)
                            flight cycles. Do all applicable corrective actions before further flight. (2) Within 3,000 flight cycles or 3 years after the effective date of this AD, replace the fitting with a new, improved fitting in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. Accomplishing the requirements of this paragraph terminates the requirements of paragraphs (g), (m), and (p)(1) of this AD for that outboard foreflap only. (q) New Inspection and Corrective Actions on Fittings Replaced According to Paragraph (k), (o), or (p) of This AD on Outboard Foreflaps For airplanes on which a new, improved carriage attach fitting on the outboard foreflap was replaced in accordance with the requirements of paragraph (k), (o), or (p) of this AD: Within 20,000 flight cycles after installing that fitting, do a detailed inspection for cracks and surface deviation on all edges surfaces, and lug attachment fastener holes, and a HFEC inspection for cracks at the lug attachment fastener holes, on the carriage attach fittings for the outboard foreflaps, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed 1,400 flight cycles. Accomplishing the requirements of this paragraph terminates the requirements of paragraph (g) of this AD for outboard foreflaps only. (r) Retained Credit for Previously Accomplished Service Bulletins (1) This paragraph restates the credit provided by paragraph (p) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with no changes. Installations accomplished before August 15, 2005 (the effective date of AD 2005-14-07), in accordance with Boeing 727 Service Bulletin 57-59, dated September 2, 1965, are acceptable for compliance with the requirements of paragraph (j)(1) of this AD. (2) This paragraph restates the credit provided by paragraph (q) of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with no changes. Inspections and modifications accomplished before August 15, 2005 (the effective date of AD 2005-14-07), in accordance with Boeing Service Bulletin 727-27-133, dated October 7, 1971, are acceptable for compliance with the requirements of paragraph (j)(2) of this AD. (s) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (t)(1) of this AD. Information may be emailed to: 
                            *9-ANM-LAACO-AMOC-Requests@faa.gov.* (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles 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. (4) AMOCs approved for AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), are approved as AMOCs for the corresponding provisions of this AD. (t) Related Information (1) For more information about this AD, contact Chandraduth Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; email 
                            *chandraduth.ramdoss@faa.gov.* (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (u)(5) and (u)(6) of this AD. (u) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on December 3, 2014. (i) Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. (ii) Reserved. (4) The following service information was approved for IBR on August 15, 2005 (70 FR 39647, July 11, 2005). (i) Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002. (ii) Boeing Service Bulletin 727-27-133, Revision 1, dated May 9, 1972. Pages 1, 12, 14 through 18, and 27 of this document are identified as Revision 1, dated May 9, 1972. Pages 2 through 11, 13, 19 through 26, and 28 are original, dated October 7, 1971. (iii) Boeing 727 Service Bulletin 57-59, Revision 1, dated September 27, 1965. Pages 1, 4, and 6 of this document are identified as Revision 1, dated September 27, 1965. Pages 2, 3, and 5 are original, dated September 2, 1965. (iv) Boeing 727 Service Bulletin 57-72, dated September 21, 1966. (5) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet 
                            *https://www.myboeingfleet.com.* (6) You may view this referenced service information at the FAA, Transport Aircraft Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: 
                            *http://www.archives.gov/​federal-register/​cfr/​ibr-locations.html.* Issued in Renton, Washington, on October 15, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.


[FR Doc. 2014-25419 Filed 10-28-14; 8:45 am] BILLING CODE 4910-13-P