Airworthiness Directives; The Boeing Company Airplanes, 40060-40063 [2013-15955]

Download as PDF 40060 Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0011, dated January 15, 2013, for related information. (2) For Airbus service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@airbus.com; Internet https:// www.airbus.com. For PPG Aerospace service information identified in this AD, contact PPG Aerospace, 12780 San Fernando Road, Sylmar, CA 91342; telephone 818 362 6711; fax 818 362 0603; Internet https:// corporateportal.ppg.com/na/aerospace. You may review copies of the 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. Issued in Renton, Washington, on June 14, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–15947 Filed 7–2–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0468; Directorate Identifier 2012–NM–147–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) that applies to certain The Boeing Company Model 777–200 and –300 series airplanes equipped with RollsRoyce engines. The existing AD currently requires repetitive inspections to detect cracks of the outer V-blades of the thrust reverser, and corrective action if necessary. The existing AD also provides for optional terminating action for the repetitive inspections. Since we issued that AD, we have received reports of cracked outer V-blade fittings at the hinge beam end of Rolls-Royce engine thrust reversers, on airplanes on tkelley on DSK3SPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 16:18 Jul 02, 2013 Jkt 229001 which the optional terminating action was done. This proposed AD would add, for airplanes on which the optional terminating action is done, repetitive inspections for cracking in the outer Vblade fittings of the hinge beam and latch beam ends of each thrust reverser half, and replacement of an affected thrust reverser half if necessary. This proposed AD would also add airplanes to the applicability. We are proposing this AD to prevent separation of a thrust reverser from the airplane during normal reverse thrust or during a refused takeoff, which could result in unexpected thrust asymmetry and a possible runway excursion. DATES: We must receive comments on this proposed AD by August 19, 2013. 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 https://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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, 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 review copies of the 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; 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 proposed 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: Melanie Violette, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6422; fax: 425–917–6590; email: melanie.violette@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2013–0468; Directorate Identifier 2012–NM–147–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On December 14, 2006, we issued AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006), for certain The Boeing Company Model 777–200 and –300 series airplanes, equipped with Rolls-Royce engines, as identified in Boeing Special Attention Service Bulletin 777–78–0064, Revision 1, dated November 30, 2006. That AD requires repetitive inspections to detect cracks of the outer V-blades of the thrust reverser, and corrective action if necessary. The existing AD also provides for optional terminating action for the repetitive inspections. That AD resulted from reports of cracked outer Vblades in the thrust reversers. We issued that AD to prevent separation of a thrust reverser from the airplane during normal reverse thrust or during a refused takeoff, which could result in impact damage to other airplane areas. If a thrust reverser separates from the airplane during a refused takeoff, the engine could produce forward thrust, resulting in unexpected thrust asymmetry and a possible runway excursion. Actions Since Existing AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006) Was Issued Since we issued AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006), we have received reports of cracked outer V-blade fittings at the hinge beam end of the thrust E:\FR\FM\03JYP1.SGM 03JYP1 40061 Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules reverser due to relative movement between the engine and the thrust reverser during flight operation, on airplanes on which the optional terminating action (Boeing Special Attention Service Bulletin 777–78– 0061, dated July 6, 2006) specified in AD 2006–26–06 had been done. Relevant Service Information We reviewed Boeing Special Attention Service Bulletins 777–78– 0061, Revision 1, dated August 28, 2007, and 777–78–0064, Revision 2, dated June 14, 2012. For information on the procedures and compliance times, see this service information at https:// www.regulations.gov by searching for Docket No. FAA–2013–0468. FAA’s Determination We are proposing 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. Proposed AD Requirements This proposed AD would retain certain requirements of AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006). This proposed AD would add new airplanes to the applicability. This proposed AD would also require, for airplanes on which the optional terminating action is done, repetitive inspections for cracking in the outer V-blade fittings of the hinge beam and latch beam ends of each thrust reverser half, and replacement of an affected thrust reverser half if necessary. The phrase ‘‘related investigative actions’’ might be used in this proposed AD. ‘‘Related investigative actions’’ are follow-on actions that: (1) Are related to the primary actions, and (2) are actions that further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. In addition, the phrase, ‘‘corrective actions’’ might be used in this proposed AD. ‘‘Corrective actions’’ are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. We have removed the reference to paragraph (h) of AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006) from paragraph (f) of AD 2006–26–06 (paragraph (g) of this proposed AD). Paragraph (h) of AD 2006–26–06 requires reporting and is not a method of compliance for doing applicable corrective actions as specified in paragraph (f) of AD 2006– 26–06. We have added a reference to paragraph (m) of this AD. Change to Existing AD Interim Action This proposed AD would retain certain requirements of AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006). Since AD 2006–26– 06 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Requirement in AD 2006– 26–06, amendment 39– 14864 (71 FR 77586, December 27, 2006) paragraph (f) ...................... paragraph (g) ..................... Corresponding requirement in this proposed AD paragraph (g) paragraph (h) We consider this proposed AD interim action. The manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we might consider additional rulemaking. Costs of Compliance We estimate that this proposed AD affects 55 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Cost per product Cost on U.S. operators Inspections [retained actions from existing AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006)]. Repetitive inspections outer V-blade [new proposed action]. 16 work-hours × $85 per hour = $1,360 per inspection cycle. $1,360 per inspection cycle. $74,800 per inspection cycle. 82 work-hours × $85 per hour = $6,970 per inspection cycle. $6,970 per inspection cycle. $383,350 per inspection cycle. We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this proposed AD. 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 PROPOSALS 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 VerDate Mar<15>2010 16:18 Jul 02, 2013 Jkt 229001 Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the 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. E:\FR\FM\03JYP1.SGM 03JYP1 40062 Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 removing airworthiness directive (AD) 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006), and adding the following new AD: ■ The Boeing Company: Docket No. FAA– 2013–0468; Directorate Identifier 2012– NM–147–AD. (a) Comments Due Date The FAA must receive comments on this AD action by August 19, 2013. (b) Affected ADs This AD supersedes AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006). (c) Applicability This AD applies to The Boeing Company Model 777–200 and –300 series airplanes, certificated in any category, equipped with Rolls-Royce engines, as identified in Boeing Special Attention Service Bulletin 777–78– 0064, Revision 2, dated June 14, 2012. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 78, Engine exhaust. (e) Unsafe Condition This AD was prompted by reports of cracked outer V-blade fittings at the hinge beam end of Rolls-Royce engine thrust reversers. We are issuing this AD to prevent separation of a thrust reverser from the airplane during normal reverse thrust or during a refused takeoff, which could result in unexpected thrust asymmetry and a possible runway excursion. tkelley on DSK3SPTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Inspections This paragraph restates the requirements of paragraph (f) of AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006), with new service information. For Group 1, Configuration 1, airplanes as identified in Boeing Special Attention Service Bulletin 777–78–0064, Revision 2, dated June 14, VerDate Mar<15>2010 16:18 Jul 02, 2013 Jkt 229001 2012: Do the detailed inspections to detect cracks in the outer V-blade of the thrust reversers. Do the inspections in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–78–0064, Revision 1, dated November 30, 2006; or Revision 2, dated June 14, 2012. Do the inspections at the applicable times specified in paragraph 1.E., ‘‘Compliance’’ of Boeing Special Attention Service Bulletin 777–78–0064, Revision 1, dated November 30, 2006; except where Boeing Special Attention Service Bulletin 777–78–0064, Revision 1, dated November 30, 2006, specifies an initial compliance time after the date on the service bulletin, this AD requires compliance within the specified time after January 11, 2007 (the effective date of AD 2006–26–06). Do applicable corrective actions before further flight, in accordance with Boeing Special Attention Service Bulletin 777–78–0064, Revision 1, dated November 30, 2006; or Revision 2, dated June 14, 2012; or paragraph (m) of this AD. As of the effective date of this AD, use only Boeing Special Attention Service Bulletin 777–78– 0064, Revision 2, dated June 14, 2012, to accomplish the actions required by this paragraph. (h) Retained Credit for Previous Actions This paragraph restates the credit for previous actions specified in paragraph (g) of AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006). For Group 1, Configuration 1, airplanes as identified in Boeing Special Attention Service Bulletin 777–78–0064, Revision 2, dated June 14, 2012: Actions done before January 11, 2007 (the effective date of AD 2006–26–06), in accordance with Boeing Special Attention Service Bulletin 777–78–0064, dated August 7, 2006, are acceptable for compliance with the requirements of paragraph (g) of this AD. (i) Retained Optional Terminating Action for Paragraph (g) of this AD with New Requirements This paragraph restates the optional terminating action specified in paragraph (i) of AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006), with new service information. Accomplishment of the actions specified in paragraph (i)(1) or (i)(2) of this AD terminates the requirements of paragraph (g) of this AD. For airplanes on which this terminating action has been accomplished, operators must do the inspection required by paragraph (j) of this AD. (1) Accomplishment of the applicable inspections and related investigative/ corrective actions before the effective date of this AD, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–78– 0061, dated July 6, 2006; except, where Boeing Special Attention Service Bulletin 777–78–0061, dated July 6, 2006, specifies to contact the manufacturer for appropriate action, repair before further flight using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (2) Accomplishment of the applicable modification, inspections, and related PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 investigative/corrective actions, in accordance with Boeing Special Attention Service Bulletin 777–78–0061, Revision 1, dated August 28, 2007; except, where Boeing Special Attention Service Bulletin 777–78– 0061, Revision 1, dated August 28, 2007, specifies to contact the manufacturer for appropriate action, repair before further flight using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (j) New Repetitive Inspections For Group 1, Configuration 2, airplanes, and Groups 2 and 3 airplanes, as identified in Boeing Special Attention Service Bulletin 777–78–0064, Revision 2, dated June 14, 2012: At the applicable times specified in paragraph 1.E., ‘‘Compliance’’ of Boeing Special Attention Service Bulletin 777–78– 0064, Revision 2, dated June 14, 2012, except as provided by paragraph (k) of this AD, do a detailed inspection for cracking of the outer V-blade fittings at the latch beam end and hinge beam end of each thrust reverser half, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–78–0064, Revision 2, dated June 14, 2012. (1) If no cracking is found, repeat the inspections thereafter at the times specified in paragraph 1.E., ‘‘Compliance’’ of Boeing Special Attention Service Bulletin 777–78– 0064, Revision 2, dated June 14, 2012. (2) If any cracking is found, before further flight, replace the affected thrust reverser half with a serviceable thrust reverser half, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–78–0064, Revision 2, dated June 14, 2012. Repeat the inspections thereafter at the times specified in paragraph 1.E., ‘‘Compliance’’ of Boeing Special Attention Service Bulletin 777–78–0064, Revision 2, dated June 14, 2012. (k) Service Information Exception Where Boeing Special Attention Service Bulletin 777–78–0064, Revision 2, dated June 14, 2012, specifies an initial compliance time ‘‘after the date of Revision 2 of this service bulletin,’’ this AD requires compliance within the specified time after the effective date of this AD. (l) Reporting Although Boeing Special Attention Service Bulletin 777–78–0064, Revision 2, dated June 14, 2012, specifies to submit certain information to the manufacturer, this AD does not include that requirement. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. E:\FR\FM\03JYP1.SGM 03JYP1 Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules (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) AMOCs approved previously in accordance with AD 2006–26–06, Amendment 39–14864 (71 FR 77586, December 27, 2006), are not approved as AMOCs for this AD. (n) Related Information (1) For more information about this AD, contact Melanie Violette, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6422; fax: 425–917– 6590; email: melanie.violette@faa.gov. (2) 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 review copies of the 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. Issued in Renton, Washington, on June 14, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–15955 Filed 7–2–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0556; Directorate Identifier 2007–SW–30–AD] RIN 2120–AA64 tkelley on DSK3SPTVN1PROD with PROPOSALS Airworthiness Directives; Erickson AirCrane Incorporated Helicopters (Type Certificate previously Held by Sikorsky Aircraft Corporation) Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) SUMMARY: VerDate Mar<15>2010 16:18 Jul 02, 2013 Jkt 229001 Model S–64E helicopters. The existing AD requires checks of the main rotor blades for a crack. This proposed AD would retain the actions of the existing AD, would reflect that the type certificate (TC) for this model helicopter has been transferred to Erickson AirCrane Incorporated (Erickson), and expand the applicability to include the similar Erickson Model S–64F helicopters. This proposed AD is prompted by a need to expand the applicability to include Model S–64F helicopters and clarify the applicable main rotor blades by part number. The proposed actions are intended to detect a crack in the main rotor blade and prevent blade separation and subsequent loss of control of the helicopter. We must receive comments on this proposed AD by September 3, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed AD, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson/Compliance Officer, 3100 Willow Springs Rd., PO Box 3247, Central Point, OR 97502; telephone (541) 664–5544; fax (541) 664–2312; email cerickson@ericksonaircrane.com. 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. PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 40063 JC Lin, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5170; email 7-AVS-ASW170@faa.gov. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. Discussion On December 6, 1990, we issued AD 90–26–12, Amendment 39–6841 (55 FR 51406, December 14, 1990) for Sikorsky Model S–64E helicopters. The AD requires repetitive checks of the Blade Inspection Method (BIM) indicator of each main rotor blade to determine whether the blade pressure has been compromised by a blade crack. These checks, which may be performed by the pilot, must be accomplished and recorded before the first flight of each day and thereafter at intervals not to exceed three hours time-in-service (TIS) for helicopters engaged in seven or more external lifts per hour or five hours TIS for operations with less than seven external lifts per hour or operations without an external load, with each check-interval measured from the last check. Those actions are intended to detect fatigue cracks in the blade, which could result in separation of the blade and loss of control of the helicopter. E:\FR\FM\03JYP1.SGM 03JYP1

Agencies

[Federal Register Volume 78, Number 128 (Wednesday, July 3, 2013)]
[Proposed Rules]
[Pages 40060-40063]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-15955]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0468; Directorate Identifier 2012-NM-147-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to certain The Boeing Company Model 777-200 and -300 
series airplanes equipped with Rolls-Royce engines. The existing AD 
currently requires repetitive inspections to detect cracks of the outer 
V-blades of the thrust reverser, and corrective action if necessary. 
The existing AD also provides for optional terminating action for the 
repetitive inspections. Since we issued that AD, we have received 
reports of cracked outer V-blade fittings at the hinge beam end of 
Rolls-Royce engine thrust reversers, on airplanes on which the optional 
terminating action was done. This proposed AD would add, for airplanes 
on which the optional terminating action is done, repetitive 
inspections for cracking in the outer V-blade fittings of the hinge 
beam and latch beam ends of each thrust reverser half, and replacement 
of an affected thrust reverser half if necessary. This proposed AD 
would also add airplanes to the applicability. We are proposing this AD 
to prevent separation of a thrust reverser from the airplane during 
normal reverse thrust or during a refused takeoff, which could result 
in unexpected thrust asymmetry and a possible runway excursion.

DATES: We must receive comments on this proposed AD by August 19, 2013.

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 https://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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, 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 review 
copies of the 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; 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 proposed 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: Melanie Violette, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6422; fax: 
425-917-6590; email: melanie.violette@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0468; 
Directorate Identifier 2012-NM-147-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On December 14, 2006, we issued AD 2006-26-06, Amendment 39-14864 
(71 FR 77586, December 27, 2006), for certain The Boeing Company Model 
777-200 and -300 series airplanes, equipped with Rolls-Royce engines, 
as identified in Boeing Special Attention Service Bulletin 777-78-0064, 
Revision 1, dated November 30, 2006. That AD requires repetitive 
inspections to detect cracks of the outer V-blades of the thrust 
reverser, and corrective action if necessary. The existing AD also 
provides for optional terminating action for the repetitive 
inspections. That AD resulted from reports of cracked outer V-blades in 
the thrust reversers. We issued that AD to prevent separation of a 
thrust reverser from the airplane during normal reverse thrust or 
during a refused takeoff, which could result in impact damage to other 
airplane areas. If a thrust reverser separates from the airplane during 
a refused takeoff, the engine could produce forward thrust, resulting 
in unexpected thrust asymmetry and a possible runway excursion.

Actions Since Existing AD 2006-26-06, Amendment 39-14864 (71 FR 77586, 
December 27, 2006) Was Issued

    Since we issued AD 2006-26-06, Amendment 39-14864 (71 FR 77586, 
December 27, 2006), we have received reports of cracked outer V-blade 
fittings at the hinge beam end of the thrust

[[Page 40061]]

reverser due to relative movement between the engine and the thrust 
reverser during flight operation, on airplanes on which the optional 
terminating action (Boeing Special Attention Service Bulletin 777-78-
0061, dated July 6, 2006) specified in AD 2006-26-06 had been done.

Relevant Service Information

    We reviewed Boeing Special Attention Service Bulletins 777-78-0061, 
Revision 1, dated August 28, 2007, and 777-78-0064, Revision 2, dated 
June 14, 2012. For information on the procedures and compliance times, 
see this service information at https://www.regulations.gov by searching 
for Docket No. FAA-2013-0468.

FAA's Determination

    We are proposing 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.

Proposed AD Requirements

    This proposed AD would retain certain requirements of AD 2006-26-
06, Amendment 39-14864 (71 FR 77586, December 27, 2006). This proposed 
AD would add new airplanes to the applicability. This proposed AD would 
also require, for airplanes on which the optional terminating action is 
done, repetitive inspections for cracking in the outer V-blade fittings 
of the hinge beam and latch beam ends of each thrust reverser half, and 
replacement of an affected thrust reverser half if necessary.
    The phrase ``related investigative actions'' might be used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that: (1) Are related to the primary actions, and (2) are actions that 
further investigate the nature of any condition found. Related 
investigative actions in an AD could include, for example, inspections.
    In addition, the phrase, ``corrective actions'' might be used in 
this proposed AD. ``Corrective actions'' are actions that correct or 
address any condition found. Corrective actions in an AD could include, 
for example, repairs.

Change to Existing AD

    This proposed AD would retain certain requirements of AD 2006-26-
06, Amendment 39-14864 (71 FR 77586, December 27, 2006). Since AD 2006-
26-06 was issued, the AD format has been revised, and certain 
paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
Requirement in AD 2006-26-06, amendment
  39-14864 (71 FR 77586, December 27,      Corresponding requirement in
                 2006)                           this proposed AD
------------------------------------------------------------------------
paragraph (f)..........................  paragraph (g)
paragraph (g)..........................  paragraph (h)
------------------------------------------------------------------------

    We have removed the reference to paragraph (h) of AD 2006-26-06, 
Amendment 39-14864 (71 FR 77586, December 27, 2006) from paragraph (f) 
of AD 2006-26-06 (paragraph (g) of this proposed AD). Paragraph (h) of 
AD 2006-26-06 requires reporting and is not a method of compliance for 
doing applicable corrective actions as specified in paragraph (f) of AD 
2006-26-06. We have added a reference to paragraph (m) of this AD.

Interim Action

    We consider this proposed AD interim action. The manufacturer is 
currently developing a modification that will address the unsafe 
condition identified in this AD. Once this modification is developed, 
approved, and available, we might consider additional rulemaking.

Costs of Compliance

    We estimate that this proposed AD affects 55 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost            Cost per product      Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained actions from     16 work-hours x $85 per  $1,360 per inspection    $74,800 per inspection
 existing AD 2006-26-06, Amendment 39-  hour = $1,360 per        cycle.                   cycle.
 14864 (71 FR 77586, December 27,       inspection cycle.
 2006)].
Repetitive inspections outer           82 work-hours x $85 per  $6,970 per inspection    $383,350 per inspection
 V[dash]blade [new proposed action].    hour = $6,970 per        cycle.                   cycle.
                                        inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

Authority for this Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

[[Page 40062]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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) 
2006-26-06, Amendment 39-14864 (71 FR 77586, December 27, 2006), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2013-0468; Directorate Identifier 
2012-NM-147-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by August 19, 
2013.

(b) Affected ADs

    This AD supersedes AD 2006-26-06, Amendment 39-14864 (71 FR 
77586, December 27, 2006).

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -300 
series airplanes, certificated in any category, equipped with Rolls-
Royce engines, as identified in Boeing Special Attention Service 
Bulletin 777-78-0064, Revision 2, dated June 14, 2012.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 78, Engine exhaust.

(e) Unsafe Condition

    This AD was prompted by reports of cracked outer V-blade 
fittings at the hinge beam end of Rolls-Royce engine thrust 
reversers. We are issuing this AD to prevent separation of a thrust 
reverser from the airplane during normal reverse thrust or during a 
refused takeoff, which could result in unexpected thrust asymmetry 
and a possible runway excursion.

(f) Compliance

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

(g) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (f) of AD 
2006-26-06, Amendment 39-14864 (71 FR 77586, December 27, 2006), 
with new service information. For Group 1, Configuration 1, 
airplanes as identified in Boeing Special Attention Service Bulletin 
777-78-0064, Revision 2, dated June 14, 2012: Do the detailed 
inspections to detect cracks in the outer V-blade of the thrust 
reversers. Do the inspections in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 777-78-
0064, Revision 1, dated November 30, 2006; or Revision 2, dated June 
14, 2012. Do the inspections at the applicable times specified in 
paragraph 1.E., ``Compliance'' of Boeing Special Attention Service 
Bulletin 777-78-0064, Revision 1, dated November 30, 2006; except 
where Boeing Special Attention Service Bulletin 777-78-0064, 
Revision 1, dated November 30, 2006, specifies an initial compliance 
time after the date on the service bulletin, this AD requires 
compliance within the specified time after January 11, 2007 (the 
effective date of AD 2006-26-06). Do applicable corrective actions 
before further flight, in accordance with Boeing Special Attention 
Service Bulletin 777-78-0064, Revision 1, dated November 30, 2006; 
or Revision 2, dated June 14, 2012; or paragraph (m) of this AD. As 
of the effective date of this AD, use only Boeing Special Attention 
Service Bulletin 777-78-0064, Revision 2, dated June 14, 2012, to 
accomplish the actions required by this paragraph.

(h) Retained Credit for Previous Actions

    This paragraph restates the credit for previous actions 
specified in paragraph (g) of AD 2006-26-06, Amendment 39-14864 (71 
FR 77586, December 27, 2006). For Group 1, Configuration 1, 
airplanes as identified in Boeing Special Attention Service Bulletin 
777-78-0064, Revision 2, dated June 14, 2012: Actions done before 
January 11, 2007 (the effective date of AD 2006-26-06), in 
accordance with Boeing Special Attention Service Bulletin 777-78-
0064, dated August 7, 2006, are acceptable for compliance with the 
requirements of paragraph (g) of this AD.

(i) Retained Optional Terminating Action for Paragraph (g) of this AD 
with New Requirements

    This paragraph restates the optional terminating action 
specified in paragraph (i) of AD 2006-26-06, Amendment 39-14864 (71 
FR 77586, December 27, 2006), with new service information. 
Accomplishment of the actions specified in paragraph (i)(1) or 
(i)(2) of this AD terminates the requirements of paragraph (g) of 
this AD. For airplanes on which this terminating action has been 
accomplished, operators must do the inspection required by paragraph 
(j) of this AD.
    (1) Accomplishment of the applicable inspections and related 
investigative/corrective actions before the effective date of this 
AD, in accordance with the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 777-78-0061, dated July 6, 2006; 
except, where Boeing Special Attention Service Bulletin 777-78-0061, 
dated July 6, 2006, specifies to contact the manufacturer for 
appropriate action, repair before further flight using a method 
approved in accordance with the procedures specified in paragraph 
(m) of this AD.
    (2) Accomplishment of the applicable modification, inspections, 
and related investigative/corrective actions, in accordance with 
Boeing Special Attention Service Bulletin 777-78-0061, Revision 1, 
dated August 28, 2007; except, where Boeing Special Attention 
Service Bulletin 777-78-0061, Revision 1, dated August 28, 2007, 
specifies to contact the manufacturer for appropriate action, repair 
before further flight using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD.

(j) New Repetitive Inspections

    For Group 1, Configuration 2, airplanes, and Groups 2 and 3 
airplanes, as identified in Boeing Special Attention Service 
Bulletin 777-78-0064, Revision 2, dated June 14, 2012: At the 
applicable times specified in paragraph 1.E., ``Compliance'' of 
Boeing Special Attention Service Bulletin 777-78-0064, Revision 2, 
dated June 14, 2012, except as provided by paragraph (k) of this AD, 
do a detailed inspection for cracking of the outer V-blade fittings 
at the latch beam end and hinge beam end of each thrust reverser 
half, in accordance with the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 777-78-0064, Revision 2, dated 
June 14, 2012.
    (1) If no cracking is found, repeat the inspections thereafter 
at the times specified in paragraph 1.E., ``Compliance'' of Boeing 
Special Attention Service Bulletin 777-78-0064, Revision 2, dated 
June 14, 2012.
    (2) If any cracking is found, before further flight, replace the 
affected thrust reverser half with a serviceable thrust reverser 
half, in accordance with the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 777-78-0064, Revision 2, dated 
June 14, 2012. Repeat the inspections thereafter at the times 
specified in paragraph 1.E., ``Compliance'' of Boeing Special 
Attention Service Bulletin 777-78-0064, Revision 2, dated June 14, 
2012.

(k) Service Information Exception

    Where Boeing Special Attention Service Bulletin 777-78-0064, 
Revision 2, dated June 14, 2012, specifies an initial compliance 
time ``after the date of Revision 2 of this service bulletin,'' this 
AD requires compliance within the specified time after the effective 
date of this AD.

(l) Reporting

    Although Boeing Special Attention Service Bulletin 777-78-0064, 
Revision 2, dated June 14, 2012, specifies to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.

[[Page 40063]]

    (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) AMOCs approved previously in accordance with AD 2006-26-06, 
Amendment 39-14864 (71 FR 77586, December 27, 2006), are not 
approved as AMOCs for this AD.

(n) Related Information

    (1) For more information about this AD, contact Melanie 
Violette, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; phone: 425-917-6422; fax: 425-917-6590; email: 
melanie.violette@faa.gov.
    (2) 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 review copies of the 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.

    Issued in Renton, Washington, on June 14, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-15955 Filed 7-2-13; 8:45 am]
BILLING CODE 4910-13-P