Airworthiness Directives; the Boeing Company Airplanes, 67052-67054 [2014-26440]

Download as PDF 67052 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 747–53A2605, Revision 3, dated July 10, 2013: This paragraph provides credit for the actions required by paragraphs (j)(1) and (k)(1) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747– 53A2605, Revision 2, dated December 9, 2011, which is not incorporated by reference in this AD. (n) 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 (o)(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. (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. (4) AMOCs approved for inspections required by AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012) are approved as AMOCs for the corresponding inspection provisions of paragraphs (g), (h), and (i) of this AD. (5) AMOCs approved for AD 2012–13–08, Amendment 39–17110 (77 FR 40481, July 10, 2012) that granted modification deviations are approved as AMOCs for the corresponding modification required by paragraph (j)(1) of this AD. wreier-aviles on DSK5TPTVN1PROD with RULES (o) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425– 917–6590; email: Nathan.P.Weigand@ faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(6) and (p)(7) of this AD. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on December 17, 2014. VerDate Sep<11>2014 14:57 Nov 10, 2014 Jkt 235001 (i) Boeing Alert Service Bulletin 747– 53A2605, Revision 3, dated July 10, 2013. (ii) Reserved. (4) The following service information was approved for IBR on August 14, 2012 (77 FR 40481, July 10, 2012). (i) Boeing Alert Service Bulletin 747– 53A2502, Revision 1, dated June 17, 2010. (ii) Reserved. (5) The following service information was approved for IBR on February 16, 2006 (71 FR 1947, January 12, 2006). (i) Boeing Special Attention Service Bulletin 747–53–2502, dated April 21, 2005. (ii) Reserved. (6) 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. (7) 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. (8) 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/ibrlocations.html. Issued in Renton, Washington, on October 28, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–26536 Filed 11–10–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0430; Directorate Identifier 2014–NM–083–AD; Amendment 39–18014; AD 2014–22–09] 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 767 airplanes. This AD was prompted by a report of a rotary actuator for the trailing edge (TE) flap that had slipped relative to its mating reaction ring, which is attached to the flap support rib. This AD requires repetitive inspections for corrosion of the fixed ring gear and reaction ring splines of the rotary actuator assembly SUMMARY: PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 for each support position, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct flap rotary actuator gear disengagement from its mating reaction ring. This disengagement with flaps extended could cause an uncommanded roll due to flap blowback, overload, or flap departure from the airplane, which could compromise safe flight and landing of the airplane. DATES: This AD is effective December 17, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 17, 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 http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0430; 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: Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6487; fax: 425–917–6590; email: Allen.Rauschendorfer@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 767 airplanes. The NPRM published in E:\FR\FM\12NOR1.SGM 12NOR1 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations the Federal Register on July 9, 2014 (79 FR 38797). The NPRM was prompted by a report of a rotary actuator for the TE flap that had slipped relative to its mating reaction ring, which is attached to the flap support rib. The NPRM proposed to require repetitive inspections for corrosion of the fixed ring gear and reaction ring splines of the rotary actuator assembly for each support position, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct flap rotary actuator gear disengagement from its mating reaction ring. This disengagement with flaps extended could cause an uncommanded roll due to flap blowback, overload, or flap departure from the airplane, which could compromise safe flight and landing of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM (79 FR 38797, July 9, 2014) and the FAA’s response to the comment. necessary to comply with the requirements of 14 CFR 39.17. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing Supplemental Type Certificate (STC) ST01920SE (http:// rgl.faa.gov/Regulatory_and_Guidance_ Library/rgstc.nsf/0/ 59027f43b9a7486e86257b1d006591ee/ $FILE/ST01920SE.pdf) does not affect the actions specified in the NPRM (79 FR 38797, July 9, 2014). We concur with the commenter. We have redesignated paragraph (c) of the NPRM (79 FR 38797, July 9, 2014) as paragraph (c)(1) and added a new paragraph (c)(2) to this AD to state that installation of STC ST01920SE (http:// rgl.faa.gov/Regulatory_and_Guidance_ Library/rgstc.nsf/0/ 59027f43b9a7486e86257b1d006591ee/ $FILE/ST01920SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not 67053 Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 38797, July 9, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 38797, July 9, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 389 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Inspection .......................... 60 work-hours × $85 per hour = $5,100 per inspection cycle. $0 We estimate the following costs to do any necessary repairs that would be Cost per product Cost on U.S. operators $5,100 per inspection cycle. required based on the results of the inspection. We have no way of $1,983,900 per inspection cycle. determining the number of aircraft that might need these repairs: ON-CONDITION COSTS Action Labor cost Parts cost Actuator repair .............................. 4 work-hours × $85 per hour = $340 per actuator ............................ $0 wreier-aviles on DSK5TPTVN1PROD with RULES 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 VerDate Sep<11>2014 14:57 Nov 10, 2014 Jkt 235001 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, PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 Cost per product $340 per actuator. (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: E:\FR\FM\12NOR1.SGM 12NOR1 67054 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2014–22–09 The Boeing Company: Amendment 39–18014 ; Docket No. FAA–2014–0430; Directorate Identifier 2014–NM–083–AD. (a) Effective Date This AD is effective December 17, 2014. (b) Affected ADs None. (c) Applicability (1) This AD applies to all The Boeing Company Model 767–200, –300, –300F, and –400ER series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01920SE (http:// rgl.faa.gov/Regulatory_and_Guidance_ Library/rgstc.nsf/0/ 59027f43b9a7486e86257b1d006591ee/$FILE/ ST01920SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE is installed, a ’’change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Unsafe Condition This AD was prompted by a report of a trailing edge (TE) flap rotary actuator that had slipped relative to its mating reaction ring, which is attached to the flap support rib. We are issuing this AD to detect and correct flap rotary actuator gear disengagement from its mating reaction ring. This disengagement with flaps extended could cause an uncommanded roll due to flap blowback, overload, or flap departure from the airplane, which could compromise safe flight and landing of the airplane. wreier-aviles on DSK5TPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections, Related Investigative Actions, and Corrective Actions Except as provided by paragraph (h) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 767–27A0229, dated March 4, 2014: Do a detailed inspection for corrosion of the rotary actuator assembly fixed ring gear and reaction ring splines for each support position; and do all applicable VerDate Sep<11>2014 14:57 Nov 10, 2014 Jkt 235001 related investigative and corrective actions if necessary; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767–27A0229, dated March 4, 2014. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the rotary actuator assembly fixed ring gear and reaction ring splines for each support position thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 767–27A0229, dated March 4, 2014. (h) Exception to the Requirements of Paragraph (g) of this AD Where paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 767–27A0229, dated March 4, 2014, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time ‘‘after the effective date of this AD.’’ (i) 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 (j) 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 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. (4) If the service information contains steps that are labeled as RC (Required for Compliance), those steps must be done to comply with this AD; any steps that are not labeled as RC are recommended. Those steps that are not labeled as RC may be deviated from, done as part of other actions, or done using accepted methods different from those identified in the specified service information without obtaining approval of an AMOC, provided the steps labeled as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to steps labeled as RC require approval of an AMOC. (j) Related Information For more information about this AD, contact Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057– PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 3356; phone: 425–917–6487; fax: 425–917– 6590; email: Allen.Rauschendorfer@faa.gov. (k) 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 767– 27A0229, dated March 4, 2014. (ii) Reserved. (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 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. (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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on October 28, 2014. Jeffrey E. Duven Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–26440 Filed 11–10–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 43 [Docket No. FAA–2000–8017, Amdt. No. 43– 38A] RIN 2120–AH11 Disposition of Life Limited Aircraft Parts; Technical Amendment Federal Aviation Administration, DOT. ACTION: Final rule; technical amendment. AGENCY: The FAA is correcting a final rule published in the Federal Register on January 15, 2002 (67 FR 2110). In that rule, the FAA amended its regulations to require that all persons who remove any life-limited aircraft part safely control that part, to deter the installation of that part after it has reached its life limit. The rule reduced the risk of life-limited parts being used SUMMARY: E:\FR\FM\12NOR1.SGM 12NOR1

Agencies

[Federal Register Volume 79, Number 218 (Wednesday, November 12, 2014)]
[Rules and Regulations]
[Pages 67052-67054]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-26440]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0430; Directorate Identifier 2014-NM-083-AD; 
Amendment 39-18014; AD 2014-22-09]
RIN 2120-AA64


Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all the 
Boeing Company Model 767 airplanes. This AD was prompted by a report of 
a rotary actuator for the trailing edge (TE) flap that had slipped 
relative to its mating reaction ring, which is attached to the flap 
support rib. This AD requires repetitive inspections for corrosion of 
the fixed ring gear and reaction ring splines of the rotary actuator 
assembly for each support position, and related investigative and 
corrective actions if necessary. We are issuing this AD to detect and 
correct flap rotary actuator gear disengagement from its mating 
reaction ring. This disengagement with flaps extended could cause an 
uncommanded roll due to flap blowback, overload, or flap departure from 
the airplane, which could compromise safe flight and landing of the 
airplane.

DATES: This AD is effective December 17, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 17, 
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 http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0430; 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: Allen Rauschendorfer, Aerospace 
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6487; fax: 425-917-6590; email: 
Allen.Rauschendorfer@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 767 airplanes. The NPRM published in

[[Page 67053]]

the Federal Register on July 9, 2014 (79 FR 38797). The NPRM was 
prompted by a report of a rotary actuator for the TE flap that had 
slipped relative to its mating reaction ring, which is attached to the 
flap support rib. The NPRM proposed to require repetitive inspections 
for corrosion of the fixed ring gear and reaction ring splines of the 
rotary actuator assembly for each support position, and related 
investigative and corrective actions if necessary. We are issuing this 
AD to detect and correct flap rotary actuator gear disengagement from 
its mating reaction ring. This disengagement with flaps extended could 
cause an uncommanded roll due to flap blowback, overload, or flap 
departure from the airplane, which could compromise safe flight and 
landing of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM (79 FR 
38797, July 9, 2014) and the FAA's response to the comment.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing stated that accomplishing Supplemental 
Type Certificate (STC) ST01920SE (http://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf) does not affect 
the actions specified in the NPRM (79 FR 38797, July 9, 2014).
    We concur with the commenter. We have redesignated paragraph (c) of 
the NPRM (79 FR 38797, July 9, 2014) as paragraph (c)(1) and added a 
new paragraph (c)(2) to this AD to state that installation of STC 
ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf) does 
not affect the ability to accomplish the actions required by this AD. 
Therefore, for airplanes on which STC ST01920SE is installed, a 
``change in product'' alternative method of compliance (AMOC) approval 
request is not necessary to comply with the requirements of 14 CFR 
39.17.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 38797, July 9, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 38797, July 9, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 389 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection......................  60 work-hours x $85              $0   $5,100 per           $1,983,900 per
                                   per hour = $5,100                     inspection cycle.    inspection cycle.
                                   per inspection
                                   cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the inspection. We have no 
way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                        Labor cost             Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Actuator repair...................  4 work-hours x $85 per                  $0   $340 per actuator.
                                     hour = $340 per actuator.
----------------------------------------------------------------------------------------------------------------

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:

[[Page 67054]]

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):

2014-22-09 The Boeing Company: Amendment 39-18014 ; Docket No. FAA-
2014-0430; Directorate Identifier 2014-NM-083-AD.

(a) Effective Date

    This AD is effective December 17, 2014.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 767-200, -
300, -300F, and -400ER series airplanes, certificated in any 
category.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01920SE is 
installed, a ''change in product'' alternative method of compliance 
(AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Unsafe Condition

    This AD was prompted by a report of a trailing edge (TE) flap 
rotary actuator that had slipped relative to its mating reaction 
ring, which is attached to the flap support rib. We are issuing this 
AD to detect and correct flap rotary actuator gear disengagement 
from its mating reaction ring. This disengagement with flaps 
extended could cause an uncommanded roll due to flap blowback, 
overload, or flap departure from the airplane, which could 
compromise safe flight and landing of the airplane.

(f) Compliance

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

(g) Repetitive Inspections, Related Investigative Actions, and 
Corrective Actions

    Except as provided by paragraph (h) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 767-27A0229, dated March 4, 2014: Do a 
detailed inspection for corrosion of the rotary actuator assembly 
fixed ring gear and reaction ring splines for each support position; 
and do all applicable related investigative and corrective actions 
if necessary; in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 767-27A0229, dated March 4, 2014. Do 
all applicable related investigative and corrective actions before 
further flight. Repeat the inspection of the rotary actuator 
assembly fixed ring gear and reaction ring splines for each support 
position thereafter at the applicable intervals specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
767-27A0229, dated March 4, 2014.

(h) Exception to the Requirements of Paragraph (g) of this AD

    Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 767-27A0229, dated March 4, 2014, specifies a compliance 
time ``after the original issue date of this service bulletin,'' 
this AD requires compliance within the specified compliance time 
``after the effective date of this AD.''

(i) 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 (j) 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.
    (4) If the service information contains steps that are labeled 
as RC (Required for Compliance), those steps must be done to comply 
with this AD; any steps that are not labeled as RC are recommended. 
Those steps that are not labeled as RC may be deviated from, done as 
part of other actions, or done using accepted methods different from 
those identified in the specified service information without 
obtaining approval of an AMOC, provided the steps labeled as RC can 
be done and the airplane can be put back in a serviceable condition. 
Any substitutions or changes to steps labeled as RC require approval 
of an AMOC.

(j) Related Information

    For more information about this AD, contact Allen 
Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; phone: 425-917-6487; fax: 425-917-6590; email: 
Allen.Rauschendorfer@faa.gov.

(k) 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 767-27A0229, dated March 4, 
2014.
    (ii) Reserved.
    (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 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.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 28, 2014.
Jeffrey E. Duven
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-26440 Filed 11-10-14; 8:45 am]
BILLING CODE 4910-13-P