Airworthiness Directives; The Boeing Company Airplanes, 55681-55684 [2012-21533]

Download as PDF 55681 Rules and Regulations Federal Register Vol. 77, No. 176 Tuesday, September 11, 2012 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1250; Directorate Identifier 2010–NM–031–AD; Amendment 39–17176; AD 2012–17–13] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 707–100 long body, –200, –100B long body, and –100B short body series airplanes; Model 707–300, –300B, –300C, and –400 series airplanes; and Model 720 and 720B series airplanes. This AD was prompted by reports of stress corrosion cracking in the chord segments made from 7079 aluminum in the horizontal stabilizer rear spar, and potential early fatigue cracking in the chord segments made from 7075 aluminum. For certain airplanes, this AD requires using redefined flight cycle counts, determining the type of material of the horizontal stabilizer, rear spar, and upper and lower chords on the inboard and outboard ends of the rear spar; repetitively inspecting for cracking of the horizontal stabilizer components; and repairing or replacing the chord, or modifying chord segments made from 7079 aluminum, if necessary. For all airplanes, this AD requires inspecting certain structurally significant items, and repairing discrepancies if necessary. We are issuing this AD to detect and correct stress corrosion and/or potential early fatigue cracking in the horizontal stabilizer, which could compromise the structural integrity of the stabilizer. sroberts on DSK5SPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 17:47 Sep 10, 2012 Jkt 226001 This AD is effective October 16, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 16, 2012. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. DATES: Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations. gov; 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 Document 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: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425– 917–6577; fax: 425–917–6590; email: berhane.alazar@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM published in the Federal Register on November 28, 2011 (76 FR 72863). For certain airplanes, that NPRM proposed to require using redefined flight cycle counts, determining the type of material of the horizontal stabilizer, rear spar, and upper and lower chords on the inboard PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 and outboard ends of the rear spar; repetitively inspecting for cracking of the horizontal stabilizer components; and repairing or replacing the chord, or modifying the chord segments made from 7079 aluminum, if necessary. For all airplanes, that NPRM also proposed to require inspecting certain structurally significant items, and repairing discrepancies if necessary. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the proposal (76 FR 72863, November 28, 2011) and the FAA’s response. Request To Correct Certain Fatigue Cracking Assertions Boeing reported that the NPRM (76 FR 72863, November 28, 2011), in various locations, stated incorrectly that fatigue cracking occurred in rear spar chords made from 7075 aluminum. According to Boeing, fatigue cracking has been reported in spar chords made from 7079 aluminum only. Boeing requested that we revise the NPRM to remove reference to ‘‘fatigue cracking’’ when addressing the failure mode of the rear spar chords made from 7075 aluminum. We partially agree with the request. Chords made from 7075 aluminum have better fatigue characteristics than those made from 7079 aluminum. But all metals fatigue to a varying degree. We have therefore revised this final rule to characterize these conditions as ‘‘potential early fatigue’’ to address Boeing’s concern and clarify that the accelerated fatigue occurrence was a consequence of abnormal use of the airplane as used in military touch-andgo training. Additional Change Made to This AD Note 1 to paragraph (i) of the NPRM (76 FR 72863, November 28, 2011) defined a special detailed inspection. We have removed that note in this final rule. A special detailed inspection is defined in Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, and it is unnecessary to repeat that definition in the AD. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD E:\FR\FM\11SER1.SGM 11SER1 55682 Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Rules and Regulations with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (76 FR 72863, November 28, 2011) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (76 FR 72863, November 28, 2011). We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Interim Action We consider this AD interim action. If final action is later identified, we might consider further rulemaking then. Costs of Compliance We estimate that this AD affects 10 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD. TABLE—ESTIMATED COSTS Action Work hours Average labor rate per hour Parts Cost per product Number of U.S.registered airplanes Fleet cost Inspections ........ 24 to 32 $85 $0 $2,040 to $2,720 per inspection cycle. 10 $20,400 to $27,200 per inspection cycle. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. 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. sroberts on DSK5SPTVN1PROD with RULES Regulatory Findings 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), VerDate Mar<15>2010 17:47 Sep 10, 2012 Jkt 226001 (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. identified in Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, and Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (e) Unsafe Condition 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 Air Transport Association (ATA) of America Code 55: Stabilizers. This AD was prompted by reports of stress corrosion cracking in the chord segments made from 7079 aluminum in the horizontal stabilizer rear spar, and potential early fatigue cracking in the chord segments made from 7075 aluminum. The Federal Aviation Administration is issuing this AD to detect and correct stress corrosion and/or potential early fatigue cracking in the horizontal stabilizer, which could compromise the structural integrity of the stabilizer. (f) Compliance 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 (d) Subject [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Flight Cycle Counting Procedure 2012–17–13 The Boeing Company: Amendment 39–17176; Docket No. FAA–2011–1250; Directorate Identifier 2010–NM–031–AD. Flight cycles, as used in this AD, must be counted as defined in Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007 (for Model airplanes); or Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008 (for Model airplanes, and Model 720 and 720B series airplanes). (a) Effective Date This AD is effective October 16, 2012. (h) Determination of Material of the Components of the Horizontal Stabilizer (b) Affected ADs This AD affects AD 85–12–01, Amendment 39–5073 (50 FR 26690, June 28, 1985), as revised by AD 85–12–01 R1, Amendment 39– 5439 (51 FR 36002, October 8, 1986). For airplanes identified in Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007: At the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD, determine the type of material of the horizontal stabilizer, rear spar, upper chords, and lower chords on the inboard and outboard ends of the rear spar, in accordance with Part 2 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. (1) Within 180 days after the effective date of this AD. (c) Applicability This AD applies to The Boeing Company Model 707-100 long body, -200, -100B long body, and -100B short body series airplanes; Model 707-300, -300B, -300C, and -400 series airplanes; and Model 720 and 720B series airplanes; certificated in any category; as PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\11SER1.SGM 11SER1 Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Rules and Regulations (2) Before further flight after any horizontal stabilizer is replaced after the effective date of this AD. (i) Repetitive Inspections of 7075 Aluminum Components For airplanes with horizontal stabilizer components made from 7075 aluminum, as determined during the inspection required by paragraph (h) of this AD: Within 180 days after the effective date of this AD, and before further flight after any replacement of the horizontal stabilizer, do a special detailed inspection for cracking of the upper chord on the inboard end of the rear spar on both the left and right side horizontal stabilizers, from stabilizer station—13.179 to 92.55, in accordance with Part 3 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. Repeat the inspections thereafter at intervals not to exceed 500 flight cycles, and before further flight after any replacement of the horizontal stabilizer, except as provided by paragraph (j) of this AD. If any cracking is found, before further flight, either repair the cracking in accordance with Part 3 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, except as required by paragraph (n) of this AD; or replace the chord with a new chord, in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. sroberts on DSK5SPTVN1PROD with RULES (j) Repetitive Inspections on Airplanes With Replaced Chord For airplanes on which the chord is replaced with a new chord in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007: Within 4,000 flight cycles after the chord replacement, do the inspections required by paragraph (i) of this AD, and repeat the inspections thereafter at the times specified in paragraph (i) of this AD. (k) Repetitive Inspections of 7079 Aluminum Components For airplanes with horizontal stabilizers that have components of the chords of the rear spar made from 7079 aluminum, as determined during the inspection required by paragraph (h) of this AD: Within 180 days after the effective date of this AD, do the actions required by paragraphs (k)(1), (k)(2), and (k)(3) of this AD, and repeat those actions at the applicable intervals specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD. (1) Do a special detailed inspection for cracking of the upper chord of the inboard side of the rear spar of both the left and right side horizontal stabilizers from stabilizer station—13.179 to 92.55, in accordance with Part 3 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. Repeat the inspection thereafter at intervals not to exceed 250 flight cycles or 180 days, whichever occurs first. If any cracking is found during any inspection required by this paragraph, before further flight, either repair the cracking, in accordance with Part 3 of the VerDate Mar<15>2010 17:47 Sep 10, 2012 Jkt 226001 Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, except as required by paragraph (n) of this AD; or replace the chord with a new chord, in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. (2) Do a high frequency eddy current inspection for cracking of the web flanges of the upper and lower chords of the rear spar in the left and right side horizontal stabilizers from stabilizer stations 92.55 to 272.55, in accordance with Part 4 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 180 days, whichever occurs first. If any cracking is found during any inspection required by this paragraph, before further flight, do the actions specified in paragraph (k)(2)(i) or (k)(2)(ii) of this AD. (i) Determine whether the cracking meets the limits specified in Part 4 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, and whether a previous repair has been done; determine if all 7079 upper and lower chord segments installed on the horizontal stabilizer have had the Part II, Group 1, Preventative Modification specified in Boeing 707 Service Bulletin 3356 done; and do all applicable repairs and modifications, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. Do the actions required by this paragraph in accordance with Part 4 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, except as required by paragraph (n) of this AD. Do all applicable repairs and modifications before further flight. (ii) Replace the chord with a new chord, in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. (3) Do low frequency eddy current (LFEC) inspections for cracking of the forward skin flanges of the upper and lower chords of the rear spar in the left and right side horizontal stabilizers from stabilizer stations—13.179 to 272.55 (for lower chords) and 92.55 to 272.55 (for upper chords), in accordance with Part 5 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. Repeat the inspections thereafter at intervals not to exceed 1,000 flight cycles or 180 days, whichever occurs first. If any cracking is found during any inspection required by this paragraph, before further flight, do the actions specified in either paragraph (k)(3)(i) or paragraph (k)(3)(ii) of this AD. (i) Repair any cracking, determine whether all 7079 upper and lower chord segments installed on the horizontal stabilizer have had the Part II—Preventative Modification specified in Boeing 707 Service Bulletin 3381 done, and do all applicable modifications, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. Do PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 55683 the actions required by this paragraph in accordance with Part 5 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, except as required by paragraph (n) of this AD. Do all applicable modifications before further flight. (ii) Replace the chord with a new chord, in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. (l) Modification/Chord Replacement For airplanes identified in Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, with horizontal stabilizers that have rear spar chord components made from 7079 aluminum and have not had embodied the modification of Part II of Boeing 707 Service Bulletin 3381, dated July 25, 1980; or Boeing 707 Service Bulletin 3381, Revision 1, dated July 31, 1981: Before further flight after determining the type of material in accordance with paragraph (h) of this AD, modify all 7079 chord segments installed on the horizontal stabilizer, in accordance with Part 5 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007; or replace the chord, in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. (m) Supplemental Structural Inspection Document Inspections For all airplanes: Within 180 days or 1,000 flight cycles after the effective date of this AD, whichever occurs first, do the inspections of the applicable structurally significant items specified in and in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008. If any cracking is found, before further flight, repair in accordance with the procedures specified in paragraph (q) of this AD. The inspections required by AD 85–12–01 R1, Amendment 39–5439 (51 FR 36002, October 8, 1986), are still required, except, as of the effective date of this AD, the flight-cycle interval for the repetitive inspections specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008, must be counted in accordance with the requirements of paragraph (g) of this AD. (n) Exception to the Service Information: Contacting FAA for Crack Repair If any cracking is found during any inspection required by this AD, and Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (q) of this AD. (o) Exception to the Service Information: Certain Compliance Procedures Where Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, specifies that operators ‘‘refer to’’ nondestructive test (NDT) procedures, the procedures must be done in accordance with the service E:\FR\FM\11SER1.SGM 11SER1 55684 Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Rules and Regulations information identified in paragraphs (o)(1), (o)(2), and (o)(3) of this AD, as applicable. (1) Figure 20, ‘‘Electrical Conductivity Measurement for Aluminum,’’ of Subject 51– 00–00, ‘‘Structures-General,’’ of Part 6—Eddy Current, of the Boeing 707/720 Nondestructive Test Manual, Document D6– 48023, Revision 118, dated July 15, 2011. (2) Subject 55–10–07, ‘‘Horizontal Stabilizer,’’ of Part 6—Eddy Current, of the Boeing 707/720 Nondestructive Test Manual, Document D6–48023, Revision 118, dated July 15, 2011. (3) Subject 51–01–00, ‘‘Orientation and Preparation for Testing’’ of Part 1—General, of the Boeing 707/720 Nondestructive Test Manual, Document D6–48023, Revision 118, dated July 15, 2011. (p) Parts Installation Prohibition As of the effective date of this AD, no person may install any horizontal stabilizer assembly with any chord segment having a part number other than that identified in paragraph 2.C.2. of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, on any airplane. (q) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-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, 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. sroberts on DSK5SPTVN1PROD with RULES (r) Related Information For more information about this AD, contact Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917– 6577; fax: 425–917–6590; email: berhane.alazar@faa.gov. (3) The following service information was approved for IBR on October 16, 2012. (i) Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. (ii) Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008. (iii) Subject 51–00–00, ‘‘Structures— General,’’ Figure 20, ‘‘Electrical Conductivity Measurement for Aluminum,’’ of Part 6— Eddy Current, of the Boeing 707/720 Nondestructive Test Manual, Document D6– 48023, Revision 118, dated July 15, 2011. The revision level of this document is identified in only the manual revision Transmittal Sheet. (iv) Subject 55–10–07, ‘‘Horizontal Stabilizer,’’ of Part 6—Eddy Current, of the Boeing 707/720 Nondestructive Test Manual, Document D6–48023, Revision 118, dated July 15, 2011. The revision level of this document is identified in only the manual revision Transmittal Sheet. (v) Subject 51–01–00, ‘‘Orientation and Preparation for Testing’’ of Part 1—General, of the Boeing 707/720 Nondestructive Test Manual, Document D6–48023, Revision 118, dated July 15, 2011. The revision level of this document is identified in only the manual revision Transmittal Sheet. (4) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; Internet https:// www.myboeingfleet.com. (5) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (6) You may also review copies of the 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 August 24, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–21533 Filed 9–10–12; 8:45 am] BILLING CODE 4910–13–P 17:47 Sep 10, 2012 Jkt 226001 PO 00000 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0927; Directorate Identifier 2012–SW–052–AD; Amendment 39–17178; AD 2012–18–02] RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 and AB412 EP helicopters with certain hoist hook assemblies (hook) installed. This AD requires inspecting the hook for correct assembly of the nut and body. This AD is prompted by a report that a hook separated from the cable of a helicopter. These actions are intended to prevent detachment of the hook from the helicopter and subsequent loss of an external load, possibly resulting in personal injury. DATES: This AD becomes effective September 26, 2012. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of September 26, 2012. We must receive comments on this AD by November 13, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: Examining the AD Docket (s) 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. VerDate Mar<15>2010 DEPARTMENT OF TRANSPORTATION You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, any comments received, and other information. The Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\11SER1.SGM 11SER1

Agencies

[Federal Register Volume 77, Number 176 (Tuesday, September 11, 2012)]
[Rules and Regulations]
[Pages 55681-55684]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-21533]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

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Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / 
Rules and Regulations

[[Page 55681]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1250; Directorate Identifier 2010-NM-031-AD; 
Amendment 39-17176; AD 2012-17-13]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 707-100 long body, -200, -100B long body, and 
-100B short body series airplanes; Model 707-300, -300B, -300C, and -
400 series airplanes; and Model 720 and 720B series airplanes. This AD 
was prompted by reports of stress corrosion cracking in the chord 
segments made from 7079 aluminum in the horizontal stabilizer rear 
spar, and potential early fatigue cracking in the chord segments made 
from 7075 aluminum. For certain airplanes, this AD requires using 
redefined flight cycle counts, determining the type of material of the 
horizontal stabilizer, rear spar, and upper and lower chords on the 
inboard and outboard ends of the rear spar; repetitively inspecting for 
cracking of the horizontal stabilizer components; and repairing or 
replacing the chord, or modifying chord segments made from 7079 
aluminum, if necessary. For all airplanes, this AD requires inspecting 
certain structurally significant items, and repairing discrepancies if 
necessary. We are issuing this AD to detect and correct stress 
corrosion and/or potential early fatigue cracking in the horizontal 
stabilizer, which could compromise the structural integrity of the 
stabilizer.

DATES: This AD is effective October 16, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of October 16, 
2012.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. 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; 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 Document 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: Berhane Alazar, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-
917-6577; fax: 425-917-6590; email: berhane.alazar@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM published in the Federal Register on November 28, 2011 (76 FR 
72863). For certain airplanes, that NPRM proposed to require using 
redefined flight cycle counts, determining the type of material of the 
horizontal stabilizer, rear spar, and upper and lower chords on the 
inboard and outboard ends of the rear spar; repetitively inspecting for 
cracking of the horizontal stabilizer components; and repairing or 
replacing the chord, or modifying the chord segments made from 7079 
aluminum, if necessary. For all airplanes, that NPRM also proposed to 
require inspecting certain structurally significant items, and 
repairing discrepancies if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the proposal 
(76 FR 72863, November 28, 2011) and the FAA's response.

Request To Correct Certain Fatigue Cracking Assertions

    Boeing reported that the NPRM (76 FR 72863, November 28, 2011), in 
various locations, stated incorrectly that fatigue cracking occurred in 
rear spar chords made from 7075 aluminum. According to Boeing, fatigue 
cracking has been reported in spar chords made from 7079 aluminum only. 
Boeing requested that we revise the NPRM to remove reference to 
``fatigue cracking'' when addressing the failure mode of the rear spar 
chords made from 7075 aluminum.
    We partially agree with the request. Chords made from 7075 aluminum 
have better fatigue characteristics than those made from 7079 aluminum. 
But all metals fatigue to a varying degree. We have therefore revised 
this final rule to characterize these conditions as ``potential early 
fatigue'' to address Boeing's concern and clarify that the accelerated 
fatigue occurrence was a consequence of abnormal use of the airplane as 
used in military touch-and-go training.

Additional Change Made to This AD

    Note 1 to paragraph (i) of the NPRM (76 FR 72863, November 28, 
2011) defined a special detailed inspection. We have removed that note 
in this final rule. A special detailed inspection is defined in Boeing 
707 Alert Service Bulletin A3515, dated December 19, 2007, and it is 
unnecessary to repeat that definition in the AD.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting the 
AD

[[Page 55682]]

with the changes described previously and minor editorial changes. We 
have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (76 FR 72863, November 28, 2011) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (76 FR 72863, November 28, 2011).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Interim Action

    We consider this AD interim action. If final action is later 
identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this AD affects 10 airplanes of U.S. registry. The 
following table provides the estimated costs for U.S. operators to 
comply with this AD.

                                                                 Table--Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                               Number of U.S.-
           Action             Work hours    Average labor     Parts      Cost per product         registered                    Fleet cost
                                            rate per hour                                         airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections................     24 to 32              $85        $0   $2,040 to $2,720 per                  10   $20,400 to $27,200 per inspection
                                                                       inspection cycle.                          cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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

    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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2012-17-13 The Boeing Company: Amendment 39-17176; Docket No. FAA-
2011-1250; Directorate Identifier 2010-NM-031-AD.

(a) Effective Date

    This AD is effective October 16, 2012.

(b) Affected ADs

    This AD affects AD 85-12-01, Amendment 39-5073 (50 FR 26690, 
June 28, 1985), as revised by AD 85-12-01 R1, Amendment 39-5439 (51 
FR 36002, October 8, 1986).

(c) Applicability

    This AD applies to The Boeing Company Model 707-100 long body, -
200, -100B long body, and -100B short body series airplanes; Model 
707-300, -300B, -300C, and -400 series airplanes; and Model 720 and 
720B series airplanes; certificated in any category; as identified 
in Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, 
and Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008.

(d) Subject

    Air Transport Association (ATA) of America Code 55: Stabilizers.

(e) Unsafe Condition

    This AD was prompted by reports of stress corrosion cracking in 
the chord segments made from 7079 aluminum in the horizontal 
stabilizer rear spar, and potential early fatigue cracking in the 
chord segments made from 7075 aluminum. The Federal Aviation 
Administration is issuing this AD to detect and correct stress 
corrosion and/or potential early fatigue cracking in the horizontal 
stabilizer, which could compromise the structural integrity of the 
stabilizer.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Flight Cycle Counting Procedure

    Flight cycles, as used in this AD, must be counted as defined in 
Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007 
(for Model airplanes); or Boeing 707 Alert Service Bulletin A3516, 
dated April 4, 2008 (for Model airplanes, and Model 720 and 720B 
series airplanes).

(h) Determination of Material of the Components of the Horizontal 
Stabilizer

    For airplanes identified in Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007: At the earlier of the times 
specified in paragraphs (h)(1) and (h)(2) of this AD, determine the 
type of material of the horizontal stabilizer, rear spar, upper 
chords, and lower chords on the inboard and outboard ends of the 
rear spar, in accordance with Part 2 of the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3515, dated 
December 19, 2007.
    (1) Within 180 days after the effective date of this AD.

[[Page 55683]]

    (2) Before further flight after any horizontal stabilizer is 
replaced after the effective date of this AD.

(i) Repetitive Inspections of 7075 Aluminum Components

    For airplanes with horizontal stabilizer components made from 
7075 aluminum, as determined during the inspection required by 
paragraph (h) of this AD: Within 180 days after the effective date 
of this AD, and before further flight after any replacement of the 
horizontal stabilizer, do a special detailed inspection for cracking 
of the upper chord on the inboard end of the rear spar on both the 
left and right side horizontal stabilizers, from stabilizer 
station--13.179 to 92.55, in accordance with Part 3 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007. Repeat the inspections thereafter at 
intervals not to exceed 500 flight cycles, and before further flight 
after any replacement of the horizontal stabilizer, except as 
provided by paragraph (j) of this AD. If any cracking is found, 
before further flight, either repair the cracking in accordance with 
Part 3 of the Accomplishment Instructions of Boeing 707 Alert 
Service Bulletin A3515, dated December 19, 2007, except as required 
by paragraph (n) of this AD; or replace the chord with a new chord, 
in accordance with Part 6 of the Accomplishment Instructions of 
Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007.

(j) Repetitive Inspections on Airplanes With Replaced Chord

    For airplanes on which the chord is replaced with a new chord in 
accordance with Part 6 of the Accomplishment Instructions of Boeing 
707 Alert Service Bulletin A3515, dated December 19, 2007: Within 
4,000 flight cycles after the chord replacement, do the inspections 
required by paragraph (i) of this AD, and repeat the inspections 
thereafter at the times specified in paragraph (i) of this AD.

(k) Repetitive Inspections of 7079 Aluminum Components

    For airplanes with horizontal stabilizers that have components 
of the chords of the rear spar made from 7079 aluminum, as 
determined during the inspection required by paragraph (h) of this 
AD: Within 180 days after the effective date of this AD, do the 
actions required by paragraphs (k)(1), (k)(2), and (k)(3) of this 
AD, and repeat those actions at the applicable intervals specified 
in paragraphs (k)(1), (k)(2), and (k)(3) of this AD.
    (1) Do a special detailed inspection for cracking of the upper 
chord of the inboard side of the rear spar of both the left and 
right side horizontal stabilizers from stabilizer station--13.179 to 
92.55, in accordance with Part 3 of the Accomplishment Instructions 
of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. 
Repeat the inspection thereafter at intervals not to exceed 250 
flight cycles or 180 days, whichever occurs first. If any cracking 
is found during any inspection required by this paragraph, before 
further flight, either repair the cracking, in accordance with Part 
3 of the Accomplishment Instructions of Boeing 707 Alert Service 
Bulletin A3515, dated December 19, 2007, except as required by 
paragraph (n) of this AD; or replace the chord with a new chord, in 
accordance with Part 6 of the Accomplishment Instructions of Boeing 
707 Alert Service Bulletin A3515, dated December 19, 2007.
    (2) Do a high frequency eddy current inspection for cracking of 
the web flanges of the upper and lower chords of the rear spar in 
the left and right side horizontal stabilizers from stabilizer 
stations 92.55 to 272.55, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007. Repeat the inspection thereafter at 
intervals not to exceed 1,000 flight cycles or 180 days, whichever 
occurs first. If any cracking is found during any inspection 
required by this paragraph, before further flight, do the actions 
specified in paragraph (k)(2)(i) or (k)(2)(ii) of this AD.
    (i) Determine whether the cracking meets the limits specified in 
Part 4 of the Accomplishment Instructions of Boeing 707 Alert 
Service Bulletin A3515, dated December 19, 2007, and whether a 
previous repair has been done; determine if all 7079 upper and lower 
chord segments installed on the horizontal stabilizer have had the 
Part II, Group 1, Preventative Modification specified in Boeing 707 
Service Bulletin 3356 done; and do all applicable repairs and 
modifications, in accordance with the Accomplishment Instructions of 
Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. Do 
the actions required by this paragraph in accordance with Part 4 of 
the Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007, except as required by paragraph (n) 
of this AD. Do all applicable repairs and modifications before 
further flight.
    (ii) Replace the chord with a new chord, in accordance with Part 
6 of the Accomplishment Instructions of Boeing 707 Alert Service 
Bulletin A3515, dated December 19, 2007.
    (3) Do low frequency eddy current (LFEC) inspections for 
cracking of the forward skin flanges of the upper and lower chords 
of the rear spar in the left and right side horizontal stabilizers 
from stabilizer stations--13.179 to 272.55 (for lower chords) and 
92.55 to 272.55 (for upper chords), in accordance with Part 5 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007. Repeat the inspections thereafter at 
intervals not to exceed 1,000 flight cycles or 180 days, whichever 
occurs first. If any cracking is found during any inspection 
required by this paragraph, before further flight, do the actions 
specified in either paragraph (k)(3)(i) or paragraph (k)(3)(ii) of 
this AD.
    (i) Repair any cracking, determine whether all 7079 upper and 
lower chord segments installed on the horizontal stabilizer have had 
the Part II--Preventative Modification specified in Boeing 707 
Service Bulletin 3381 done, and do all applicable modifications, in 
accordance with the Accomplishment Instructions of Boeing 707 Alert 
Service Bulletin A3515, dated December 19, 2007. Do the actions 
required by this paragraph in accordance with Part 5 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007, except as required by paragraph (n) 
of this AD. Do all applicable modifications before further flight.
    (ii) Replace the chord with a new chord, in accordance with Part 
6 of the Accomplishment Instructions of Boeing 707 Alert Service 
Bulletin A3515, dated December 19, 2007.

(l) Modification/Chord Replacement

    For airplanes identified in Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007, with horizontal stabilizers that 
have rear spar chord components made from 7079 aluminum and have not 
had embodied the modification of Part II of Boeing 707 Service 
Bulletin 3381, dated July 25, 1980; or Boeing 707 Service Bulletin 
3381, Revision 1, dated July 31, 1981: Before further flight after 
determining the type of material in accordance with paragraph (h) of 
this AD, modify all 7079 chord segments installed on the horizontal 
stabilizer, in accordance with Part 5 of the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3515, dated 
December 19, 2007; or replace the chord, in accordance with Part 6 
of the Accomplishment Instructions of Boeing 707 Alert Service 
Bulletin A3515, dated December 19, 2007.

(m) Supplemental Structural Inspection Document Inspections

    For all airplanes: Within 180 days or 1,000 flight cycles after 
the effective date of this AD, whichever occurs first, do the 
inspections of the applicable structurally significant items 
specified in and in accordance with the Accomplishment Instructions 
of Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008. If 
any cracking is found, before further flight, repair in accordance 
with the procedures specified in paragraph (q) of this AD. The 
inspections required by AD 85-12-01 R1, Amendment 39-5439 (51 FR 
36002, October 8, 1986), are still required, except, as of the 
effective date of this AD, the flight-cycle interval for the 
repetitive inspections specified in paragraph 1.E., ``Compliance,'' 
of Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008, 
must be counted in accordance with the requirements of paragraph (g) 
of this AD.

(n) Exception to the Service Information: Contacting FAA for Crack 
Repair

    If any cracking is found during any inspection required by this 
AD, and Boeing 707 Alert Service Bulletin A3515, dated December 19, 
2007, specifies to contact Boeing for appropriate action: Before 
further flight, repair the cracking using a method approved in 
accordance with the procedures specified in paragraph (q) of this 
AD.

(o) Exception to the Service Information: Certain Compliance Procedures

    Where Boeing 707 Alert Service Bulletin A3515, dated December 
19, 2007, specifies that operators ``refer to'' nondestructive test 
(NDT) procedures, the procedures must be done in accordance with the 
service

[[Page 55684]]

information identified in paragraphs (o)(1), (o)(2), and (o)(3) of 
this AD, as applicable.
    (1) Figure 20, ``Electrical Conductivity Measurement for 
Aluminum,'' of Subject 51-00-00, ``Structures-General,'' of Part 6--
Eddy Current, of the Boeing 707/720 Nondestructive Test Manual, 
Document D6-48023, Revision 118, dated July 15, 2011.
    (2) Subject 55-10-07, ``Horizontal Stabilizer,'' of Part 6--Eddy 
Current, of the Boeing 707/720 Nondestructive Test Manual, Document 
D6-48023, Revision 118, dated July 15, 2011.
    (3) Subject 51-01-00, ``Orientation and Preparation for 
Testing'' of Part 1--General, of the Boeing 707/720 Nondestructive 
Test Manual, Document D6-48023, Revision 118, dated July 15, 2011.

(p) Parts Installation Prohibition

    As of the effective date of this AD, no person may install any 
horizontal stabilizer assembly with any chord segment having a part 
number other than that identified in paragraph 2.C.2. of Boeing 707 
Alert Service Bulletin A3515, dated December 19, 2007, on any 
airplane.

(q) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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 the Related Information 
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-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, 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.

(r) Related Information

    For more information about this AD, contact Berhane Alazar, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6577; fax: 425-917-6590; email: berhane.alazar@faa.gov.

(s) 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 
October 16, 2012.
    (i) Boeing 707 Alert Service Bulletin A3515, dated December 19, 
2007.
    (ii) Boeing 707 Alert Service Bulletin A3516, dated April 4, 
2008.
    (iii) Subject 51-00-00, ``Structures--General,'' Figure 20, 
``Electrical Conductivity Measurement for Aluminum,'' of Part 6--
Eddy Current, of the Boeing 707/720 Nondestructive Test Manual, 
Document D6-48023, Revision 118, dated July 15, 2011. The revision 
level of this document is identified in only the manual revision 
Transmittal Sheet.
    (iv) Subject 55-10-07, ``Horizontal Stabilizer,'' of Part 6--
Eddy Current, of the Boeing 707/720 Nondestructive Test Manual, 
Document D6-48023, Revision 118, dated July 15, 2011. The revision 
level of this document is identified in only the manual revision 
Transmittal Sheet.
    (v) Subject 51-01-00, ``Orientation and Preparation for 
Testing'' of Part 1--General, of the Boeing 707/720 Nondestructive 
Test Manual, Document D6-48023, Revision 118, dated July 15, 2011. 
The revision level of this document is identified in only the manual 
revision Transmittal Sheet.
    (4) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (5) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (6) You may also review copies of the 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 August 24, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-21533 Filed 9-10-12; 8:45 am]
BILLING CODE 4910-13-P