80 FR 27069 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 91 (May 12, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 91 (May 12, 2015)
| Page Range | 27069-27072 | |
| FR Document | 2015-11137 |
[Federal Register Volume 80, Number 91 (Tuesday, May 12, 2015)] [Rules and Regulations] [Pages 27069-27072] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-11137] ======================================================================== 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. ======================================================================== Federal Register / Vol. 80, No. 91 / Tuesday, May 12, 2015 / Rules and Regulations [[Page 27069]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1278; Directorate Identifier 2014-NM-223-AD; Amendment 39-18155; AD 2015-09-09] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2004-07-11 for all The Boeing Company Model 767-400ER series airplanes. AD 2004-07-11 requires repetitive high frequency eddy current (HFEC) inspections of the aft lower lugs of the deflection control track of the outboard flap for cracks, and replacement of any cracked deflection control track with a new track assembly. This AD retains those requirements, provides optional terminating action for the repetitive inspections, and adds airplane models to the applicability. This AD was prompted by our determination that additional airplane models require repetitive HFEC inspections of the aft lower lugs of the deflection control track of the outboard flap for cracks, and replacement of any cracked deflection control track with a new track assembly. We are issuing this AD to detect and correct fatigue cracking in the aft lower lug run-out region of the deflection control track, which could result in the loss of the secondary load path for the outboard flap, resulting in the loss of the outboard flap and consequent reduced controllability of the airplane in the event that the primary load path also fails. DATES: This AD is effective May 27, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 27, 2015. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of May 11, 2004 (69 FR 17911, April 6, 2004). We must receive any comments on this AD by June 26, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-1278. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1278; 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 street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6577; fax: 425-917-6590; email: berhane.alazar@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On March 22, 2004, we issued AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004), for all The Boeing Company Model 767-400ER series airplanes. AD 2004-07-11 required repetitive HFEC inspections of the aft lower lugs of the deflection control track of the outboard flap for cracks, and replacement of any cracked deflection control track with a new track assembly. AD 2004-07-11 resulted from reports of fatigue cracking in the aft lower lug run-out region of the deflection control track. We issued AD 2004-07-11 to detect and correct fatigue cracking of the deflection control track, which could result in the loss of the secondary load path for the outboard flap, resulting in the loss of the outboard flap and consequent reduced controllability of the airplane in the event that the primary load path also fails. Actions Since AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004) Was Issued Since we issued AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004), we have determined that additional airplane models are subject to the identified unsafe condition. The flap installations on certain Model 767-200 and -300 series airplanes, serial numbers 922 through 933 inclusive, are identical to those installed on Model 767- 400ER series airplanes. Therefore, all of these models may be subject to the identified unsafe condition. We are issuing this AD to detect and correct fatigue cracking in the aft lower lug run-out region of the deflection control track, which could result in the loss of the secondary load path for the outboard flap, resulting in the loss of the outboard [[Page 27070]] flap and consequent reduced controllability of the airplane in the event that the primary load path also fails, on certain Model 767-200 and -300 series airplanes, serial numbers 922 through 933 inclusive. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014. The service information describes procedures for repetitive HFEC inspections of the aft lower lugs of the deflection control track of the outboard flap for cracks, and replacement of any cracked deflection control track with a new track assembly, part number 113T8333-9, which eliminates the need for the repetitive HFEC inspections. This service information is reasonably available at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1278. Or see ADDRESSES for other ways to access this service information. FAA's Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD retains all of the requirements of AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004). This AD continues to require repetitive HFEC inspections of the aft lower lugs of the deflection control track of the outboard flap for cracks, and replacement of any cracked deflection control track with a new track assembly. This AD adds airplane models to the applicability, and provides optional terminating action for the repetitive HFEC inspections even if no crack is found. Change to AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004) Since AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004) was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph designations have been redesignated in this AD, as listed in the following table: Revised Paragraph Designations ------------------------------------------------------------------------ Requirement in AD 2004-07-11, Amendment 39-13555 (69 FR 17911, Corresponding requirement in this April 6, 2004) AD ------------------------------------------------------------------------ paragraph (a) paragraph (g) paragraph (b) paragraph (h) paragraph (c) paragraph (i) ------------------------------------------------------------------------ Clarification of Paragraph (c) of AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004) We have added a reference to paragraph (h) of this AD to the corrective action requirements of paragraph (i) of this AD (which we referred to as paragraph (c) of AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004)). We have made this change to clarify the corrective action. FAA's Justification and Determination of the Effective Date This AD revises the applicability by adding airplanes that are not on the U.S. Register. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include Docket No. FAA-2015-1278 and directorate identifier 2014-NM-223-AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance The actions specified by this AD were previously required by AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004), which was applicable to approximately 38 airplanes. The actions required by AD 2004-07-11 take about 5 work-hours per airplane. In consideration of the compliance time and effective date of AD 2004-07-11, we assume that operators of the 38 airplanes subject to that AD have already initiated the required actions. This AD would add no new costs associated with the airplanes of U.S. registry, but would be applicable to approximately 11 additional airplanes of the affected design in the worldwide fleet. The current costs for this AD are repeated for the convenience of affected operators, as follows: Estimated Costs--Required Actions ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Retained inspections from AD 5 work-hours x $85 $0 $425 per inspection $16,150 per 2004-07-11, Amendment 39-13555 per hour = $425 cycle. inspection cycle. (69 FR 17911, April 6, 2004). per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate that it would take about 12 work-hours to do any necessary replacement that would be required based on the results of the inspection. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. We have no way of determining the number of aircraft that might need these actions. 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 [[Page 27071]] 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 part 39 of the Federal Aviation Regulations (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 removing Airworthiness Directive (AD) 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004) and adding the following new AD: 2015-09-09 The Boeing Company: Amendment 39-18155; Docket No. FAA- 2015-1278; Directorate Identifier 2014-NM-223-AD. (a) Effective Date This AD is effective May 27, 2015. (b) Affected ADs This AD replaces AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004). (c) Applicability This AD applies to The Boeing Company Model 767-200, -300, and - 400ER series airplanes, certificated in any category, as identified in Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls; 57, Wings. (e) Unsafe Condition This AD was prompted by our determination that additional airplane models require repetitive high frequency eddy current (HFEC) inspections of the aft lower lugs of the deflection control track of the outboard flap for cracks, and replacement of any cracked deflection control track with a new track assembly. We are issuing this AD to detect and correct fatigue cracking in the aft lower lug run-out region of the deflection control track, which could result in the loss of the secondary load path for the outboard flap, resulting in the loss of the outboard flap and consequent reduced controllability of the airplane in the event that the primary load path also fails. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Initial Inspection for Model 767-400ER Series Airplanes This paragraph restates the requirements of paragraph (a) of AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004), with revised service information. For airplanes identified in Group 1 in Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014: Before the accumulation of 12,000 total flight cycles, or within 1,200 flight cycles after May 11, 2004 (the effective date of AD 2004-07-11), whichever occurs later, perform an HFEC inspection for cracks in the aft lower lug of the deflection control track on the outboard flap, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0183, dated May 9, 2002; or Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014. As of the effective date of this AD, only Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014, may be used. (h) Retained Repetitive Inspections With New Service Information This paragraph restates the requirements of paragraph (b) of AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004), with new service information. For airplanes identified in Group 1 in Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014: If no crack is detected during any HFEC inspection required in paragraph (g) of this AD, repeat the inspection at intervals not to exceed 1,200 flight cycles. (i) Retained Corrective Action and Added Terminating Action This paragraph restates the requirements of paragraph (c) of AD 2004-07-11, Amendment 39-13555 (69 FR 17911, April 6, 2004), with revised service information, added terminating action, and added paragraph reference. For airplanes identified in Group 1 in Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014: If any crack is detected during any HFEC inspection required by paragraph (g) or (h) of this AD, before further flight, replace the deflection control track with a new track assembly, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0183, dated May 9, 2002; or Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014. Within 12,000 flight cycles following the replacement of deflection control track with a deflection control track, part number (P/N) 113T7333-3 or 113T8333-7, perform the HFEC inspection specified in paragraph (g) of this AD, and repeat inspections as specified in paragraph (h) of this AD until the deflection control track is replaced with a deflection control track, P/N 113T8333-9, as specified in paragraph (m) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014, may be used. (j) New Initial Inspection for Model 767-200 and -300 Series Airplanes For airplanes identified in Group 2 in Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014: Before the accumulation of 12,000 total flight cycles, or within 1,200 flight cycles after the effective date of this AD, whichever occurs later, do an HFEC inspection for cracks in the aft lower lug of the deflection control track on the outboard flap, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767- 27A0183, Revision 2, dated September 25, 2014. (k) New Repetitive Inspections For airplanes identified in Group 2 in Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014: If no crack is detected during any HFEC inspection required in paragraph (j) of this AD, repeat the inspection thereafter at intervals not to exceed 1,200 flight cycles. (l) New Corrective Action and Terminating Action For airplanes identified in Group 2 in Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014: If any crack is detected during any HFEC inspection required by paragraph (j) or (k) of this AD, before further flight, replace the deflection control track with a new track assembly, part number 113T8333-9, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014. This replacement terminates the inspection requirements of paragraphs (j) and (k) of this AD. (m) Optional Terminating Action Replacement of the deflection control track with a new track assembly, P/N 113T8333- [[Page 27072]] 9, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014, terminates the inspection requirements of paragraphs (g), (h), (j), and (k) of this AD. (n) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraphs (g), (h), (i), and (m) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 767-27A0183, Revision 1, dated April 4, 2014, which is not incorporated by reference in this AD. (o) 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 (p)(1) 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. (p) Related Information (1) For more information about this AD, contact Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6577; fax: 425-917-6590; email: berhane.alazar@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(5) and (q)(6) of this AD. (q) 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 May 27, 2015. (i) Boeing Service Bulletin 767-27A0183, Revision 2, dated September 25, 2014. (ii) Reserved. (4) The following service information was approved for IBR on May 11, 2004, (69 FR 17911, April 6, 2004). (i) Boeing Alert Service Bulletin 767-27A0183, dated May 9, 2002. (ii) Reserved. (5) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. (6) You may view this 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on April 29, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-11137 Filed 5-11-15; 8:45 am] BILLING CODE 4910-13-P
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Rules and Regulations Federal Register
Vol. 80, No. 91
Tuesday, May 12, 2015
This section of the FEDERAL REGISTER DATES: This AD is effective May 27, evaluation, any comments received, and
contains regulatory documents having general 2015. other information. The street address for
applicability and legal effect, most of which The Director of the Federal Register the Docket Office (phone: 800–647–
are keyed to and codified in the Code of approved the incorporation by reference 5527) is in the ADDRESSES section.
Federal Regulations, which is published under of a certain publication listed in this AD Comments will be available in the AD
50 titles pursuant to 44 U.S.C. 1510.
as of May 27, 2015. docket shortly after receipt.
The Code of Federal Regulations is sold by The Director of the Federal Register FOR FURTHER INFORMATION CONTACT:
the Superintendent of Documents. Prices of approved the incorporation by reference Berhane Alazar, Aerospace Engineer,
new books are listed in the first FEDERAL of a certain other publication listed in Airframe Branch, ANM–120S, FAA,
REGISTER issue of each week. this AD as of May 11, 2004 (69 FR Seattle Aircraft Certification Office
17911, April 6, 2004). (ACO), 1601 Lind Avenue SW., Renton,
We must receive any comments on WA 98057–3356; phone: 425–917–6577;
DEPARTMENT OF TRANSPORTATION this AD by June 26, 2015. fax: 425–917–6590; email:
ADDRESSES: You may send comments, berhane.alazar@faa.gov.
Federal Aviation Administration
using the procedures found in 14 CFR SUPPLEMENTARY INFORMATION:
14 CFR Part 39 11.43 and 11.45, by any of the following
methods: Discussion
[Docket No. FAA–2015–1278; Directorate • Federal eRulemaking Portal: Go to On March 22, 2004, we issued AD
Identifier 2014–NM–223–AD; Amendment http://www.regulations.gov. Follow the 2004–07–11, Amendment 39–13555 (69
39–18155; AD 2015–09–09] instructions for submitting comments. FR 17911, April 6, 2004), for all The
• Fax: 202–493–2251. Boeing Company Model 767–400ER
RIN 2120–AA64
• Mail: U.S. Department of series airplanes. AD 2004–07–11
Airworthiness Directives; The Boeing Transportation, Docket Operations, required repetitive HFEC inspections of
Company Airplanes M–30, West Building Ground Floor, the aft lower lugs of the deflection
Room W12–140, 1200 New Jersey control track of the outboard flap for
AGENCY: Federal Aviation Avenue SE., Washington, DC 20590. cracks, and replacement of any cracked
Administration (FAA), DOT. • Hand Delivery: U.S. Department of deflection control track with a new track
ACTION: Final rule; request for Transportation, Docket Operations, assembly. AD 2004–07–11 resulted from
comments. M–30, West Building Ground Floor, reports of fatigue cracking in the aft
Room W12–140, 1200 New Jersey lower lug run-out region of the
SUMMARY: We are superseding Avenue SE., Washington, DC 20590, deflection control track. We issued AD
Airworthiness Directive (AD) 2004–07– between 9 a.m. and 5 p.m., Monday 2004–07–11 to detect and correct fatigue
11 for all The Boeing Company Model through Friday, except Federal holidays. cracking of the deflection control track,
767–400ER series airplanes. AD 2004– For service information identified in which could result in the loss of the
07–11 requires repetitive high frequency this AD, contact Boeing Commercial secondary load path for the outboard
eddy current (HFEC) inspections of the Airplanes, Attention: Data & Services flap, resulting in the loss of the outboard
aft lower lugs of the deflection control Management, P.O. Box 3707, MC 2H–65, flap and consequent reduced
track of the outboard flap for cracks, and Seattle, WA 98124–2207; telephone controllability of the airplane in the
replacement of any cracked deflection 206–544–5000, extension 1; fax 206– event that the primary load path also
control track with a new track assembly. 766–5680; Internet https:// fails.
This AD retains those requirements, www.myboeingfleet.com. You may view
provides optional terminating action for Actions Since AD 2004–07–11,
this referenced service information at
the repetitive inspections, and adds Amendment 39–13555 (69 FR 17911,
the FAA, Transport Airplane
airplane models to the applicability. April 6, 2004) Was Issued
Directorate, 1601 Lind Avenue SW.,
This AD was prompted by our Renton, WA. For information on the Since we issued AD 2004–07–11,
determination that additional airplane availability of this material at the FAA, Amendment 39–13555 (69 FR 17911,
models require repetitive HFEC call 425–227–1221. It is also available April 6, 2004), we have determined that
inspections of the aft lower lugs of the on the Internet at http:// additional airplane models are subject
deflection control track of the outboard www.regulations.gov by searching for to the identified unsafe condition. The
flap for cracks, and replacement of any and locating Docket No. FAA–2015– flap installations on certain Model 767–
cracked deflection control track with a 1278. 200 and –300 series airplanes, serial
new track assembly. We are issuing this numbers 922 through 933 inclusive, are
AD to detect and correct fatigue Examining the AD Docket identical to those installed on Model
cracking in the aft lower lug run-out You may examine the AD docket on 767–400ER series airplanes. Therefore,
region of the deflection control track, the Internet at http:// all of these models may be subject to the
mstockstill on DSK4VPTVN1PROD with RULES
which could result in the loss of the www.regulations.gov by searching for identified unsafe condition. We are
secondary load path for the outboard and locating Docket No. FAA–2015– issuing this AD to detect and correct
flap, resulting in the loss of the outboard 1278; or in person at the Docket fatigue cracking in the aft lower lug run-
flap and consequent reduced Management Facility between 9 a.m. out region of the deflection control
controllability of the airplane in the and 5 p.m., Monday through Friday, track, which could result in the loss of
event that the primary load path also except Federal holidays. The AD docket the secondary load path for the outboard
fails. contains this AD, the regulatory flap, resulting in the loss of the outboard
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![Federal Register / Vol. 80, No. 91 / Tuesday, May 12, 2015 / Rules and Regulations 27071
promoting safe flight of civil aircraft in (b) Affected ADs (i) Retained Corrective Action and Added
air commerce by prescribing regulations This AD replaces AD 2004–07–11, Terminating Action
for practices, methods, and procedures Amendment 39–13555 (69 FR 17911, April 6, This paragraph restates the requirements of
the Administrator finds necessary for 2004). paragraph (c) of AD 2004–07–11,
safety in air commerce. This regulation Amendment 39–13555 (69 FR 17911, April 6,
(c) Applicability
is within the scope of that authority 2004), with revised service information,
This AD applies to The Boeing Company added terminating action, and added
because it addresses an unsafe condition Model 767–200, -300, and -400ER series paragraph reference. For airplanes identified
that is likely to exist or develop on airplanes, certificated in any category, as in Group 1 in Boeing Service Bulletin 767–
products identified in this rulemaking identified in Boeing Service Bulletin 767– 27A0183, Revision 2, dated September 25,
action. 27A0183, Revision 2, dated September 25, 2014: If any crack is detected during any
2014. HFEC inspection required by paragraph (g) or
Regulatory Findings (h) of this AD, before further flight, replace
(d) Subject
This AD will not have federalism the deflection control track with a new track
Air Transport Association (ATA) of assembly, in accordance with the
implications under Executive Order America Code 27, Flight controls; 57, Wings. Accomplishment Instructions of Boeing Alert
13132. This AD will not have a
(e) Unsafe Condition Service Bulletin 767–27A0183, dated May 9,
substantial direct effect on the States, on 2002; or Boeing Service Bulletin 767–
the relationship between the national This AD was prompted by our
27A0183, Revision 2, dated September 25,
government and the States, or on the determination that additional airplane
2014. Within 12,000 flight cycles following
distribution of power and models require repetitive high frequency
the replacement of deflection control track
eddy current (HFEC) inspections of the aft
responsibilities among the various lower lugs of the deflection control track of
with a deflection control track, part number
levels of government. (P/N) 113T7333–3 or 113T8333–7, perform
the outboard flap for cracks, and replacement
For the reasons discussed above, I of any cracked deflection control track with the HFEC inspection specified in paragraph
certify that this AD: a new track assembly. We are issuing this AD (g) of this AD, and repeat inspections as
to detect and correct fatigue cracking in the specified in paragraph (h) of this AD until the
(1) Is not a ‘‘significant regulatory deflection control track is replaced with a
action’’ under Executive Order 12866, aft lower lug run-out region of the deflection
control track, which could result in the loss deflection control track, P/N 113T8333–9, as
(2) Is not a ‘‘significant rule’’ under of the secondary load path for the outboard specified in paragraph (m) of this AD. As of
DOT Regulatory Policies and Procedures flap, resulting in the loss of the outboard flap the effective date of this AD, only Boeing
(44 FR 11034, February 26, 1979), and consequent reduced controllability of the Service Bulletin 767–27A0183, Revision 2,
(3) Will not affect intrastate aviation airplane in the event that the primary load dated September 25, 2014, may be used.
in Alaska, and path also fails. (j) New Initial Inspection for Model 767–200
(4) Will not have a significant (f) Compliance and –300 Series Airplanes
economic impact, positive or negative, Comply with this AD within the For airplanes identified in Group 2 in
on a substantial number of small entities compliance times specified, unless already Boeing Service Bulletin 767–27A0183,
under the criteria of the Regulatory done. Revision 2, dated September 25, 2014: Before
Flexibility Act. the accumulation of 12,000 total flight cycles,
(g) Retained Initial Inspection for Model or within 1,200 flight cycles after the
List of Subjects in 14 CFR Part 39 767–400ER Series Airplanes effective date of this AD, whichever occurs
This paragraph restates the requirements of later, do an HFEC inspection for cracks in the
Air transportation, Aircraft, Aviation aft lower lug of the deflection control track
paragraph (a) of AD 2004–07–11,
safety, Incorporation by reference, Amendment 39–13555 (69 FR 17911, April 6, on the outboard flap, in accordance with the
Safety. 2004), with revised service information. For Accomplishment Instructions of Boeing
Adoption of the Amendment airplanes identified in Group 1 in Boeing Service Bulletin 767–27A0183, Revision 2,
Service Bulletin 767–27A0183, Revision 2, dated September 25, 2014.
Accordingly, under the authority dated September 25, 2014: Before the
(k) New Repetitive Inspections
delegated to me by the Administrator, accumulation of 12,000 total flight cycles, or
the FAA amends part 39 of the Federal within 1,200 flight cycles after May 11, 2004 For airplanes identified in Group 2 in
(the effective date of AD 2004–07–11), Boeing Service Bulletin 767–27A0183,
Aviation Regulations (14 CFR part 39) as Revision 2, dated September 25, 2014: If no
whichever occurs later, perform an HFEC
follows: crack is detected during any HFEC inspection
inspection for cracks in the aft lower lug of
the deflection control track on the outboard required in paragraph (j) of this AD, repeat
PART 39—AIRWORTHINESS flap, in accordance with the Accomplishment the inspection thereafter at intervals not to
DIRECTIVES Instructions of Boeing Alert Service Bulletin exceed 1,200 flight cycles.
767–27A0183, dated May 9, 2002; or Boeing
■ 1. The authority citation for part 39 (l) New Corrective Action and Terminating
Service Bulletin 767–27A0183, Revision 2,
continues to read as follows: Action
dated September 25, 2014. As of the effective
date of this AD, only Boeing Service Bulletin For airplanes identified in Group 2 in
Authority: 49 U.S.C. 106(g), 40113, 44701.
767–27A0183, Revision 2, dated September Boeing Service Bulletin 767–27A0183,
§ 39.13 [Amended] 25, 2014, may be used. Revision 2, dated September 25, 2014: If any
crack is detected during any HFEC inspection
(h) Retained Repetitive Inspections With required by paragraph (j) or (k) of this AD,
■ 2. The FAA amends § 39.13 by
New Service Information before further flight, replace the deflection
removing Airworthiness Directive (AD)
2004–07–11, Amendment 39–13555 (69 This paragraph restates the requirements of control track with a new track assembly, part
paragraph (b) of AD 2004–07–11, number 113T8333–9, in accordance with the
FR 17911, April 6, 2004) and adding the
Amendment 39–13555 (69 FR 17911, April 6, Accomplishment Instructions of Boeing
following new AD:
mstockstill on DSK4VPTVN1PROD with RULES
2004), with new service information. For Service Bulletin 767–27A0183, Revision 2,
2015–09–09 The Boeing Company: airplanes identified in Group 1 in Boeing dated September 25, 2014. This replacement
Amendment 39–18155; Docket No. Service Bulletin 767–27A0183, Revision 2, terminates the inspection requirements of
FAA–2015–1278; Directorate Identifier dated September 25, 2014: If no crack is paragraphs (j) and (k) of this AD.
2014–NM–223–AD. detected during any HFEC inspection
required in paragraph (g) of this AD, repeat (m) Optional Terminating Action
(a) Effective Date the inspection at intervals not to exceed Replacement of the deflection control track
This AD is effective May 27, 2015. 1,200 flight cycles. with a new track assembly, P/N 113T8333–
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![27072 Federal Register / Vol. 80, No. 91 / Tuesday, May 12, 2015 / Rules and Regulations
9, in accordance with the Accomplishment (i) Boeing Alert Service Bulletin 767– The Director of the Federal Register
Instructions of Boeing Service Bulletin 767– 27A0183, dated May 9, 2002. approved the incorporation by reference
27A0183, Revision 2, dated September 25, (ii) Reserved. of certain other publications listed in
2014, terminates the inspection requirements (5) For service information identified in
this AD as of February 9, 2015 (80 FR
of paragraphs (g), (h), (j), and (k) of this AD. this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services 155, January 5, 2015).
(n) Credit for Previous Actions Management, P.O. Box 3707, MC 2H–65, ADDRESSES: You may examine the AD
This paragraph provides credit for the Seattle, WA 98124–2207; telephone 206– docket on the Internet at http://
actions specified in paragraphs (g), (h), (i), 544–5000, extension 1; fax 206–766–5680; www.regulations.gov by searching for
and (m) of this AD, if those actions were Internet https://www.myboeingfleet.com.
performed before the effective date of this AD (6) You may view this service information
and locating Docket No. FAA–2015–
using Boeing Service Bulletin 767–27A0183, at FAA, Transport Airplane Directorate, 1601 0415; or in person at the Docket
Revision 1, dated April 4, 2014, which is not Lind Avenue SW., Renton, WA. For Management Facility, U.S. Department
incorporated by reference in this AD. information on the availability of this of Transportation, Docket Operations,
material at the FAA, call 425–227–1221. M–30, West Building Ground Floor,
(o) Alternative Methods of Compliance (7) You may view this service information Room W12–140, 1200 New Jersey
(AMOCs) that is incorporated by reference at the Avenue SE., Washington, DC 20590.
(1) The Manager, Seattle Aircraft National Archives and Records
Certification Office (ACO), FAA, has the Administration (NARA). For information on For service information identified in
authority to approve AMOCs for this AD, if the availability of this material at NARA, call this AD, contact Grob Aircraft AG,
requested using the procedures found in 14 202–741–6030, or go to: http:// Customer Service, Lettenbachstrasse 9,
CFR 39.19. In accordance with 14 CFR 39.19, www.archives.gov/federal-register/cfr/ibr- D–86874 Tussenhausen-Mattsies,
send your request to your principal inspector locations.html. Germany, telephone: + 49 (0) 8268–998–
or local Flight Standards District Office, as 105; fax: + 49 (0) 8268–998–200; email:
Issued in Renton, Washington, on April 29,
appropriate. If sending information directly productsupport@grob-aircraft.com;
2015.
to the manager of the ACO, send it to the Internet: grob-aircraft.com. You may
attention of the person identified in Jeffrey E. Duven,
Manager, Transport Airplane Directorate, view this referenced service information
paragraph (p)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOC- Aircraft Certification Service. at the FAA, Small Airplane Directorate,
Requests@faa.gov. [FR Doc. 2015–11137 Filed 5–11–15; 8:45 am]
901 Locust, Kansas City, Missouri
(2) Before using any approved AMOC, 64106. For information on the
BILLING CODE 4910–13–P
notify your appropriate principal inspector, availability of this material at the FAA,
or lacking a principal inspector, the manager call (816) 329–4148. It is also available
of the local flight standards district office/ on the Internet at http://
DEPARTMENT OF TRANSPORTATION
certificate holding district office. www.regulations.gov by searching for
(3) An AMOC that provides an acceptable and locating Docket No. FAA–2015–
Federal Aviation Administration
level of safety may be used for any repair
0415.
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization 14 CFR Part 39
FOR FURTHER INFORMATION CONTACT: Karl
Designation Authorization (ODA) that has [Docket No. FAA–2015–0415; Directorate Schletzbaum, Aerospace Engineer, FAA,
been authorized by the Manager, Seattle Identifier 2015–CE–001–AD; Amendment
ACO, to make those findings. For a repair
Small Airplane Directorate, 901 Locust,
39–18152; AD 2015–09–06] Room 301, Kansas City, Missouri 64106;
method to be approved, the repair must meet
the certification basis of the airplane and the RIN 2120–AA64 telephone: (816) 329–4123; fax: (816)
approval must specifically refer to this AD. 329–4090; email: karl.schletzbaum@
Airworthiness Directives; GROB– faa.gov.
(p) Related Information
WERKE Airplanes
(1) For more information about this AD, SUPPLEMENTARY INFORMATION:
contact Berhane Alazar, Aerospace Engineer, AGENCY: Federal Aviation
Airframe Branch, ANM–120S, FAA, Seattle Discussion
Administration (FAA), Department of
Aircraft Certification Office (ACO), 1601 Lind Transportation (DOT). We issued a notice of proposed
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6577; fax: 425–917–6590; ACTION: Final rule. rulemaking (NPRM) to amend 14 CFR
email: berhane.alazar@faa.gov. part 39 to add an AD that would apply
(2) Service information identified in this SUMMARY: We are superseding to certain GROB–WERKE Models
AD that is not incorporated by reference is Airworthiness Directive (AD) 2014–26– G115EG and G120A airplanes. That
available at the addresses specified in 04 for certain GROB–WERKE Models NPRM was published in the Federal
paragraphs (q)(5) and (q)(6) of this AD. G115EG and G120A airplanes. This AD Register on February 26, 2015 (80 FR
results from mandatory continuing 10423), and proposed to supersede AD
(q) Material Incorporated by Reference
airworthiness information (MCAI) 2014–26–04, Amendment 39–18055 (80
(1) The Director of the Federal Register issued by an aviation authority of
approved the incorporation by reference
FR 155, January 5, 2015).
another country to identify and correct The NPRM proposed to correct an
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR an unsafe condition on an aviation unsafe condition for the specified
part 51. product. The MCAI describes the unsafe products and was based on mandatory
(2) You must use this service information condition as a defective starter solenoid. continuing airworthiness information
as applicable to do the actions required by We are issuing this AD to require (MCAI) originated by an aviation
this AD, unless the AD specifies otherwise. actions to address the unsafe condition authority of another country. The MCAI
mstockstill on DSK4VPTVN1PROD with RULES
(3) The following service information was on these products.
approved for IBR on May 27, 2015. states:
DATES: This AD is effective June 16,
(i) Boeing Service Bulletin 767–27A0183, An operator of a G 115E aeroplane
Revision 2, dated September 25, 2014. 2015. experienced a total loss of electrical power in
(ii) Reserved. The Director of the Federal Register flight. The investigation found that a
(4) The following service information was approved the incorporation by reference defective starter solenoid had caused an
approved for IBR on May 11, 2004, (69 FR of certain publications listed in the AD internal short circuit which resulted in
17911, April 6, 2004). as of June 16, 2015. breakdown of the system voltage.
VerDate Sep<11>2014 16:43 May 11, 2015 Jkt 235001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\12MYR1.SGM 12MYR1](https://thefederalregister.org/doc/80_FR_27160/page/4.svg)
Document Created: 2015-12-16 07:55:31
Document Modified: 2015-12-16 07:55:31
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD is effective May 27, 2015. | |
| Contact | Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6577; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 27069 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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