Airworthiness Directives; The Boeing Company Airplanes, 17405-17408 [2014-06776]

Download as PDF Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD): 2008–08–25, Amendment 39–15479 (73 FR 21240, April 21, 2008), and adding the following new AD: ■ 2014–05–31 The Boeing Company: Amendment 39–17803; Docket No. FAA–2012–0862; Directorate Identifier 2011–NM–198–AD. (a) Effective Date This AD is effective May 2, 2014. (b) Affected ADs This AD supersedes AD 2008–08–25, Amendment 39–15479 (73 FR 21240, April 21, 2008). (c) Applicability This AD applies to The Boeing Company airplanes, certificated in any category, as specified in paragraphs (c)(1) and (c)(2) of this AD. (1) Model 747–400F series airplanes, as identified in Boeing Alert Service Bulletin 747–25A3580, Revision 2, dated May 13, 2013. (2) Model 747–400 series airplanes, as identified in Boeing Alert Service Bulletin 747–25A3581, Revision 1, dated June 30, 2011. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/Furnishings. (e) Unsafe Condition This AD was prompted by reports of continued water damage to diode fire card 285U0072–1 in the M826 automatic fire overheat logic test system cardfile following a false FWD CARGO FIRE message, with no change in frequency, which resulted in an air turn back. We are issuing this AD to prevent water from exiting over the edge of the existing drip shield and contaminating electrical components in the M826 cardfile, which could result in an electrical short and potential loss of several functions essential for safe flight. tkelley on DSK3SPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Installation and Replacement Within 24 months after the effective date of this AD, install aft and forward drain tubes, relocate wire bundle routing, install a new drip shield and drip shield deflectors, and replace insulation blankets, in accordance with the Accomplishment Instructions of the service information identified in paragraph (g)(1), (g)(2), or (g)(3); as applicable; of this AD. (1) (For Model 747–400F series airplanes) Boeing Alert Service Bulletin 747–25A3580, Revision 2, dated May 13, 2013. (2) (For Model 747–400 series airplanes) Boeing Alert Service Bulletin 747–25A3581, Revision 1, dated June 30, 2011. (3) (For Model 747–400 series airplanes) Boeing Alert Service Bulletin 747–25A3581, VerDate Mar<15>2010 16:20 Mar 27, 2014 Jkt 232001 Revision 2, dated September 11, 2012 (for Model 747–400 series airplanes). (h) Concurrent Actions For Group 1 airplanes as identified in Boeing Alert Service Bulletin 747–25A3581, Revision 1, dated June 30, 2011: Prior to or concurrently with the actions required by paragraph (g) of this AD, seal the drain slot, install spuds, and install left- and right-side drain tubes, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–25A3526, Revision 1, dated February 20, 2009 (for Model 747–400 series airplanes), except as specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Steps 1 through 5 of Figure 2 of Boeing Alert Service Bulletin 747–25A3526, Revision 1, dated February 20, 2009, are not required if work is being accomplished concurrently with the actions specified in Boeing Alert Service Bulletin 747–25A3581, Revision 1, dated June 30, 2011 (for Model 747–400 series airplanes). (2) The portion of ‘‘More Data’’ in step 8 of Figure 3 of Boeing Alert Service Bulletin 747–25A3526, Revision 1, dated February 20, 2009, which says ‘‘Attach drain tube and strap above bead on the spud,’’ is not required. (i) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747–25A3580, Revision 1, dated July 14, 2011, which is not incorporated by reference in this AD. (j) 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 paragraph (k)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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. (k) Related Information (1) For more information about this AD, contact Francis Smith, Aerospace Engineer, Cabin Safety & Environmental Control Systems, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6596; fax: 425–917–6590; email: francis.smith@faa.gov. (2) Service information identified in this AD that is not incorporated by reference in this AD may be obtained at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 17405 (l) 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. (i) Boeing Alert Service Bulletin 747– 25A3526, Revision 1, dated February 20, 2009. (ii) Boeing Alert Service Bulletin 747– 25A3580, Revision 2, dated May 13, 2013. (iii) Boeing Alert Service Bulletin 747– 25A3581, Revision 1, dated June 30, 2011. (iv) Boeing Alert Service Bulletin 747– 25A3581, Revision 2, dated September 11, 2012. (3) For Boeing 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. (4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA 98057–3356. For information on the availability of this material at the FAA, call 425–227–1221. (5) 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on March 5, 2014. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–05558 Filed 3–27–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0701; Directorate Identifier 2013–NM–073–AD; Amendment 39–17768; AD 2014–04–09] 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 all The Boeing Company Model 727 airplanes. This AD will complete certain mandated programs intended to support the airplane reaching its limit of validity SUMMARY: E:\FR\FM\28MRR1.SGM 28MRR1 17406 Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations tkelley on DSK3SPTVN1PROD with RULES (LOV) of the engineering data that support the established structural maintenance program. This AD requires repetitive inspections for cracking of small repairs done on the vertical flange of the rib chord, repetitive inspections for cracking along the upper fillet radius of the rib chord, and a large repair or preventive modification if necessary. Accomplishment of a large repair or preventive modification terminates the actions of this AD. We are issuing this AD to prevent cracks in the rib upper chord, which could result in the inability of the wing structure to support the limit load condition, and consequent loss of structural integrity of the wing. DATES: This AD is effective May 2, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 2, 2014. 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 Airplane 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2013– 0701; 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 (ACO), 3960 Paramount Blvd., Suite 100, Lakewood, CA 90712–4137, phone: 562–627–5329; fax: 562–627– 5210; email: Chandraduth.Ramdoss@ faa.gov. SUPPLEMENTARY INFORMATION: VerDate Mar<15>2010 16:20 Mar 27, 2014 Jkt 232001 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 727 airplanes. The NPRM published in the Federal Register on August 27, 2013 (78 FR 52875). The NPRM proposed to require repetitive inspections for cracking of small repairs done on the vertical flange of the rib chord, repetitive inspections for cracking along the upper fillet radius of the rib chord, and a large repair or preventive modification if necessary. Accomplishment of a large repair or preventive modification would terminate the actions of the NPRM. We are issuing this AD to prevent cracks in the rib upper chord, which could result in the inability of the wing structure to support the limit load condition, and consequent loss of structural integrity of the wing. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (78 FR 52875, August 27, 2013) and the FAA’s response to each comment. Request To Remove Statement of Difference Between NPRM (78 FR 52875, August 27, 2013) and Service Information Boeing requested that we revise ‘‘Differences Between the Proposed AD and the Service Information’’ in the NPRM (78 FR 52875, August 27, 2013) to instead state that there are no differences. Boeing stated that the NPRM specified the same type, location, and interval of the inspections specified in Boeing Service Bulletin 727–57– 0112, Revision 5, dated July 31, 1997, for a small repair. We find that clarification of the requirements of this final rule is necessary in light of the information provided in Boeing Service Bulletin 727–57–0112, Revision 5, dated July 31, 1997. The post-small-repair inspection is described in Part III of the service information; some of this information is provided in notes, and the description of the area to be inspected needed slight clarification. To ensure that operators understand that all actions specified in Part III are required for compliance, and to give more specific direction to the area of inspection, paragraph (g) in this final rule specifies these actions, including the information in the notes, with slightly different wording to describe the inspection area. Since the PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 inspection is a direct requirement of this final rule, there is a difference between this AD and the service information. We have not changed this final rule regarding this issue. Request To Refer to a Single Service Information Source Paragraph (g) of the NPRM (78 FR 52875, August 27, 2013) referred to actions specified in ‘‘Boeing 727 Service Bulletin 57–112; or Part III of the Accomplishment Instructions of Boeing Service Bulletin 727–57–0112.’’ Boeing stated that only one of these references is required. Boeing added that one of the references did not follow the standard format. Boeing therefore requested that we revise the NPRM to refer to only ‘‘Part III of the Accomplishment Instructions of Boeing Service Bulletin 727–57–0112.’’ We disagree to revise the source of service information as cited in this final rule. We are required by OFR regulations to precisely specify all possible revisions of this service bulletin by their unique identities. Boeing Service Bulletin 727–57–0112 has actually been revised five times; some versions are old and were published in Boeing’s older service bulletin format. The earlier version (‘‘Boeing 727 Service Bulletin 57–112’’) does not have a separate ‘‘Accomplishment Instructions’’ section. Two citations are therefore necessary to refer to the description of the small repair actions in the service information. However, we have added Note 1 to paragraph (g) of this final rule to clarify the use of the different document citations. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the change described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (78 FR 52875, August 27, 2013) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 52875, August 27, 2013). Costs of Compliance We estimate that this AD affects 106 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\28MRR1.SGM 28MRR1 Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 17407 ESTIMATED COSTS Action Labor cost Parts cost Inspections (per wing) ... 6 work-hours × $85 per hour = $510 per inspection cycle. $0 Cost on U.S. operators Cost per product $510 per inspection cycle. Up to $108,120 per inspection cycle per airplane. ON-CONDITION COSTS Action Labor cost Parts cost Large repair 1 2 ................................. Preventive modification 1 3 ............... 300 work-hours × $85 per hour = $25,500 ............................................... 57 work-hours × $85 per hour = $4,845 ................................................... $12,139 10,614 Cost per product $37,639 15,459 1 Cost for on-condition actions (either 2 or 3), per wing. for large repair, per wing. 3 Cost for preventive modification, per wing. 2 Cost 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. tkelley on DSK3SPTVN1PROD 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), (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 VerDate Mar<15>2010 16:20 Mar 27, 2014 Jkt 232001 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 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2014–04–09 The Boeing Company: Amendment 39–17768; Docket No. FAA–2013–0701; Directorate Identifier 2013–NM–073–AD. (a) Effective Date This AD is effective May 2, 2014. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 727, 727C, 727–100, 727– 100C, 727–200, and 727–200F series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD will complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 structural maintenance program. We are issuing this AD to prevent cracks in the rib upper chord, which could result in the inability of the wing structure to support the limit load condition, and consequent loss of structural integrity of the wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Post-Repair Inspection For any small repair that has been done as specified in Boeing 727 Service Bulletin 57– 112; or Part III of the Accomplishment Instructions of Boeing Service Bulletin 727– 57–0112: Within 3,500 flight cycles after the small repair was installed or inspected as specified in Boeing Service Bulletin 727–57– 0112, or within 18 months after the effective date of this AD, whichever occurs latest, do a high frequency eddy current inspection for cracking of the vertical flange of the rib chord from the inboard side, and do a detailed (close visual) inspection for cracking along the upper fillet radius of the rib chord, in accordance with Part III of the Accomplishment Instructions of Boeing Service Bulletin 727–57–0112, Revision 5, dated July 31, 1997. Repeat the inspections thereafter at intervals not to exceed 3,500 flight cycles until accomplishment of the repair or modification specified in paragraph (i) or (j) of this AD. Note 1 to paragraph (g) of this AD: Boeing 727 Service Bulletin 57–112 and Boeing Service Bulletin 727–57–0112 are both versions of the same document. The formatting of service bulletins was revised by Boeing following publication of Boeing 727 Service Bulletin 57–112, Revision 1, dated April 23, 1976. Boeing Service Bulletin 727– 57–0112, Revision 2, dated May 19, 1988, was published using Boeing’s revised formatting. (h) Inspection Definition For the purposes of this AD, a detailed inspection is an intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an E:\FR\FM\28MRR1.SGM 28MRR1 17408 Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required. (i) Corrective Action for Cracks If any crack is found during any inspection required by paragraph (g) of this AD, before further flight, do either action specified in paragraph (i)(1) or (i)(2) of this AD. Accomplishment of either action terminates the requirements of paragraph (g) of this AD. (1) Do a large repair, in accordance with Part IV of the Accomplishment Instructions of Boeing Service Bulletin 727–57–0112, Revision 5, dated July 31, 1997. (2) Do a preventive modification, in accordance with Part V of the Accomplishment Instructions of Boeing Service Bulletin 727–57–0112, Revision 5, dated July 31, 1997. (j) Optional Terminating Action Accomplishment of the actions specified in either paragraph (j)(1) or (j)(2) of this AD terminates the requirements of paragraphs (g) and (i) of this AD. (1) A large repair, in accordance with Part IV of the Accomplishment Instructions of Boeing Service Bulletin 727–57–0112, Revision 5, dated July 31, 1997. Any crack found must be repaired before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (2) A preventive modification, in accordance with Part V of the Accomplishment Instructions of Boeing Service Bulletin 727–57–0112, Revision 5, dated July 31, 1997. Any crack found must be repaired before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. tkelley on DSK3SPTVN1PROD with RULES (k) Credit for Previous Actions This paragraph provides credit for the inspections, large repair, and modification specified in this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 727–57–0112, Revision 4, dated October 29, 1992. (l) 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 (m) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 VerDate Mar<15>2010 16:20 Mar 27, 2014 Jkt 232001 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. (m) Related Information For more information about this AD, contact Chandraduth Ramdoss, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Blvd., Suite 100, Lakewood, CA 90712–4137, phone: 562– 627–5329; fax: 562–627–5210; email: Chandraduth.Ramdoss@faa.gov. (n) 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. (i) Boeing Service Bulletin 727–57–0112, Revision 5, dated July 31, 1997. (ii) Reserved. (3) 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. (4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) 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 https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on February 14, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–06776 Filed 3–27–14; 8:45 am] BILLING CODE 4910–13–P PO 00000 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0822; Directorate Identifier 2013–SW–004–AD; Amendment 39–17783; AD 2014–05–10] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) (Airbus Helicopters) Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2012–25– 04 for Eurocopter France Model AS350B3 helicopters with a certain modification (MOD) installed. AD 2012– 25–04 required installing two placards and revising the Rotorcraft Flight Manual (RFM). AD 2012–25–04 also required certain checks and inspecting and replacing, if necessary, all four laminated half-bearings (bearings). This new AD retains the previous AD requirements, requires certain modifications which would be terminating action for the airspeed limitations, and adds certain helicopter models to the bearing inspection with a different inspection interval. These actions are intended to prevent vibration due to a failed bearing, failure of the tail rotor, and subsequent loss of control of the helicopter. DATES: This AD is effective May 2, 2014. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of May 2, 2014. ADDRESSES: For service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbushelicopters.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov in Docket No. FAA–2013–0822 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 foreign Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\28MRR1.SGM 28MRR1

Agencies

[Federal Register Volume 79, Number 60 (Friday, March 28, 2014)]
[Rules and Regulations]
[Pages 17405-17408]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-06776]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0701; Directorate Identifier 2013-NM-073-AD; 
Amendment 39-17768; AD 2014-04-09]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all The 
Boeing Company Model 727 airplanes. This AD will complete certain 
mandated programs intended to support the airplane reaching its limit 
of validity

[[Page 17406]]

(LOV) of the engineering data that support the established structural 
maintenance program. This AD requires repetitive inspections for 
cracking of small repairs done on the vertical flange of the rib chord, 
repetitive inspections for cracking along the upper fillet radius of 
the rib chord, and a large repair or preventive modification if 
necessary. Accomplishment of a large repair or preventive modification 
terminates the actions of this AD. We are issuing this AD to prevent 
cracks in the rib upper chord, which could result in the inability of 
the wing structure to support the limit load condition, and consequent 
loss of structural integrity of the wing.

DATES: This AD is effective May 2, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 2, 2014.

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 Airplane 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0701; 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 (ACO), 3960 Paramount Blvd., Suite 100, Lakewood, 
CA 90712-4137, phone: 562-627-5329; 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 by adding an AD that would apply to all The Boeing Company 
Model 727 airplanes. The NPRM published in the Federal Register on 
August 27, 2013 (78 FR 52875). The NPRM proposed to require repetitive 
inspections for cracking of small repairs done on the vertical flange 
of the rib chord, repetitive inspections for cracking along the upper 
fillet radius of the rib chord, and a large repair or preventive 
modification if necessary. Accomplishment of a large repair or 
preventive modification would terminate the actions of the NPRM. We are 
issuing this AD to prevent cracks in the rib upper chord, which could 
result in the inability of the wing structure to support the limit load 
condition, and consequent loss of structural integrity of the wing.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(78 FR 52875, August 27, 2013) and the FAA's response to each comment.

Request To Remove Statement of Difference Between NPRM (78 FR 52875, 
August 27, 2013) and Service Information

    Boeing requested that we revise ``Differences Between the Proposed 
AD and the Service Information'' in the NPRM (78 FR 52875, August 27, 
2013) to instead state that there are no differences. Boeing stated 
that the NPRM specified the same type, location, and interval of the 
inspections specified in Boeing Service Bulletin 727-57-0112, Revision 
5, dated July 31, 1997, for a small repair.
    We find that clarification of the requirements of this final rule 
is necessary in light of the information provided in Boeing Service 
Bulletin 727-57-0112, Revision 5, dated July 31, 1997. The post-small-
repair inspection is described in Part III of the service information; 
some of this information is provided in notes, and the description of 
the area to be inspected needed slight clarification. To ensure that 
operators understand that all actions specified in Part III are 
required for compliance, and to give more specific direction to the 
area of inspection, paragraph (g) in this final rule specifies these 
actions, including the information in the notes, with slightly 
different wording to describe the inspection area. Since the inspection 
is a direct requirement of this final rule, there is a difference 
between this AD and the service information. We have not changed this 
final rule regarding this issue.

Request To Refer to a Single Service Information Source

    Paragraph (g) of the NPRM (78 FR 52875, August 27, 2013) referred 
to actions specified in ``Boeing 727 Service Bulletin 57-112; or Part 
III of the Accomplishment Instructions of Boeing Service Bulletin 727-
57-0112.'' Boeing stated that only one of these references is required. 
Boeing added that one of the references did not follow the standard 
format. Boeing therefore requested that we revise the NPRM to refer to 
only ``Part III of the Accomplishment Instructions of Boeing Service 
Bulletin 727-57-0112.''
    We disagree to revise the source of service information as cited in 
this final rule. We are required by OFR regulations to precisely 
specify all possible revisions of this service bulletin by their unique 
identities. Boeing Service Bulletin 727-57-0112 has actually been 
revised five times; some versions are old and were published in 
Boeing's older service bulletin format. The earlier version (``Boeing 
727 Service Bulletin 57-112'') does not have a separate 
``Accomplishment Instructions'' section. Two citations are therefore 
necessary to refer to the description of the small repair actions in 
the service information. However, we have added Note 1 to paragraph (g) 
of this final rule to clarify the use of the different document 
citations.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the change described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 52875, August 27, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 52875, August 27, 2013).

Costs of Compliance

    We estimate that this AD affects 106 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

[[Page 17407]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
             Action                    Labor cost       Parts cost    Cost per product    Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections (per wing)..........  6 work-hours x $85            $0  $510 per inspection  Up to $108,120 per
                                   per hour = $510                   cycle.               inspection cycle per
                                   per inspection                                         airplane.
                                   cycle.
----------------------------------------------------------------------------------------------------------------


                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Large repair \1\ \2\.......................  300 work-hours x $85 per hour =             $12,139         $37,639
                                              $25,500.
Preventive modification \1\ \3\............  57 work-hours x $85 per hour =               10,614          15,459
                                              $4,845.
----------------------------------------------------------------------------------------------------------------
\1\ Cost for on-condition actions (either \2\ or \3\), per wing.
\2\ Cost for large repair, per wing.
\3\ Cost for preventive modification, per wing.

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):

2014-04-09 The Boeing Company: Amendment 39-17768; Docket No. FAA-
2013-0701; Directorate Identifier 2013-NM-073-AD.

(a) Effective Date

    This AD is effective May 2, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 727, 727C, 727-
100, 727-100C, 727-200, and 727-200F series airplanes, certificated 
in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD will complete certain mandated programs intended to 
support the airplane reaching its limit of validity (LOV) of the 
engineering data that support the established structural maintenance 
program. We are issuing this AD to prevent cracks in the rib upper 
chord, which could result in the inability of the wing structure to 
support the limit load condition, and consequent loss of structural 
integrity of the wing.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Post-Repair Inspection

    For any small repair that has been done as specified in Boeing 
727 Service Bulletin 57-112; or Part III of the Accomplishment 
Instructions of Boeing Service Bulletin 727-57-0112: Within 3,500 
flight cycles after the small repair was installed or inspected as 
specified in Boeing Service Bulletin 727-57-0112, or within 18 
months after the effective date of this AD, whichever occurs latest, 
do a high frequency eddy current inspection for cracking of the 
vertical flange of the rib chord from the inboard side, and do a 
detailed (close visual) inspection for cracking along the upper 
fillet radius of the rib chord, in accordance with Part III of the 
Accomplishment Instructions of Boeing Service Bulletin 727-57-0112, 
Revision 5, dated July 31, 1997. Repeat the inspections thereafter 
at intervals not to exceed 3,500 flight cycles until accomplishment 
of the repair or modification specified in paragraph (i) or (j) of 
this AD.
    Note 1 to paragraph (g) of this AD: Boeing 727 Service Bulletin 
57-112 and Boeing Service Bulletin 727-57-0112 are both versions of 
the same document. The formatting of service bulletins was revised 
by Boeing following publication of Boeing 727 Service Bulletin 57-
112, Revision 1, dated April 23, 1976. Boeing Service Bulletin 727-
57-0112, Revision 2, dated May 19, 1988, was published using 
Boeing's revised formatting.

(h) Inspection Definition

    For the purposes of this AD, a detailed inspection is an 
intensive examination of a specific item, installation, or assembly 
to detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at an

[[Page 17408]]

intensity deemed appropriate. Inspection aids such as mirror, 
magnifying lenses, etc., may be necessary. Surface cleaning and 
elaborate procedures may be required.

(i) Corrective Action for Cracks

    If any crack is found during any inspection required by 
paragraph (g) of this AD, before further flight, do either action 
specified in paragraph (i)(1) or (i)(2) of this AD. Accomplishment 
of either action terminates the requirements of paragraph (g) of 
this AD.
    (1) Do a large repair, in accordance with Part IV of the 
Accomplishment Instructions of Boeing Service Bulletin 727-57-0112, 
Revision 5, dated July 31, 1997.
    (2) Do a preventive modification, in accordance with Part V of 
the Accomplishment Instructions of Boeing Service Bulletin 727-57-
0112, Revision 5, dated July 31, 1997.

(j) Optional Terminating Action

    Accomplishment of the actions specified in either paragraph 
(j)(1) or (j)(2) of this AD terminates the requirements of 
paragraphs (g) and (i) of this AD.
    (1) A large repair, in accordance with Part IV of the 
Accomplishment Instructions of Boeing Service Bulletin 727-57-0112, 
Revision 5, dated July 31, 1997. Any crack found must be repaired 
before further flight using a method approved in accordance with the 
procedures specified in paragraph (l) of this AD.
    (2) A preventive modification, in accordance with Part V of the 
Accomplishment Instructions of Boeing Service Bulletin 727-57-0112, 
Revision 5, dated July 31, 1997. Any crack found must be repaired 
before further flight using a method approved in accordance with the 
procedures specified in paragraph (l) of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for the inspections, large 
repair, and modification specified in this AD, if those actions were 
performed before the effective date of this AD using Boeing Service 
Bulletin 727-57-0112, Revision 4, dated October 29, 1992.

(l) 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 (m) 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, 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.

(m) Related Information

    For more information about this AD, contact Chandraduth Ramdoss, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office (ACO), 3960 Paramount Blvd., Suite 
100, Lakewood, CA 90712-4137, phone: 562-627-5329; fax: 562-627-
5210; email: Chandraduth.Ramdoss@faa.gov.

(n) 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.

(i) Boeing Service Bulletin 727-57-0112, Revision 5, dated July 31, 
1997.
(ii) Reserved.
    (3) 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.
    (4) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) 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 https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-06776 Filed 3-27-14; 8:45 am]
BILLING CODE 4910-13-P
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