Airworthiness Directives; The Boeing Company Airplanes, 77157-77159 [2011-31738]

Download as PDF 77157 Proposed Rules Federal Register Vol. 76, No. 238 Monday, December 12, 2011 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1319; Directorate Identifier 2011–NM–143–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 777–200 and –300 series airplanes equipped with Rolls-Royce RB211 Trent 800 engines. This proposed AD was prompted by reports of events related to thermal damage of the thrust reverser (T/R) inner wall on Rolls-Royce RB211 Trent 800 engines. This proposed AD would require replacing the bleed valve parts and tubing with new parts and tubing on the left and right engines. Additionally, this proposed AD would require installing Aero-Engine database (AEDB) software in the airplane information management system (AIMS) hardware. We are proposing this AD to eliminate T/R thermal damage caused by excessive heat downstream of the 8th stage IP8 exhaust ports, which could result in T/R structural failure. This failure could result in large pieces of the T/R or adjacent components departing the airplane. A separated T/R piece could result in a rejected takeoff (RTO) and cause asymmetric thrust and consequent loss of control of the airplane during reverse thrust operations. Separated components could also cause structural damage to the airplane, damage to other airplanes, or injury to people on the ground. DATES: We must receive comments on this proposed AD by January 26, 2012. ADDRESSES: You may send comments, using the procedures found in 14 CFR mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 18:11 Dec 09, 2011 Jkt 226001 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 Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; phone: (206) 544–5000, extension 1; fax: (206) 766–5680; email: me.boecom@boeing.com; Internet: https://www.myboeingfleet.com. For Rolls-Royce service information identified in this AD, contact RollsRoyce plc, P.O. Box 31, DERBY, DE24 8BJ, UK; telephone 011 44 1332 242424; fax 011 44 1332 249936. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call (425) 227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at 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: Rebel Nichols, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6509; fax: (425) 917–6590; email: Rebel.Nichols@faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2011–1319; Directorate Identifier 2011– NM–143–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 We have received 14 reports of events related to thermal damage of the T/R inner wall on Rolls-Royce RB211 Trent 800 engines. The events have included air turnbacks, in-flight engine shutdowns, T/R inner wall panel sections and parts being separated from the airplane, collapse of the inner T/R inner wall panel, and engine fire loop fault messages. Boeing issued Alert Service Bulletin 777–78A0059, dated February 24, 2005; and Special Attention Service Bulletin 777–78–0060, dated February 24, 2005; to provide instructions for inspecting the T/R inner wall panel structure and sealing the insulation blankets to prevent hot under-cowl air from contacting the T/R inner wall panel. Since those service bulletins were released, there have been four T/R events on airplanes on which those service bulletins had not been fully accomplished and 10 T/R events on airplanes on which those service bulletins had been accomplished. There are two separate causes of the thermal degradation. The first cause is the IP8 exhaust washing the outer side of the inner wall. This cause is addressed by this proposed AD through modification of the IP8 bleed system. The second cause is the inadequate thermal protection system. We are considering further rulemaking to address this cause. E:\FR\FM\12DEP1.SGM 12DEP1 77158 Federal Register / Vol. 76, No. 238 / Monday, December 12, 2011 / Proposed Rules This thermal degradation, if not corrected, could result in the T/R being damaged by excessive heat, which could result in thrust reverser structural failure. This failure could result in large pieces of the T/R or adjacent components departing the airplane. A separated T/R piece could result in an RTO and cause asymmetric thrust and consequent loss of control of the airplane during reverse thrust operations. Separated components could also cause structural damage to the airplane, damage to other airplanes, or injury to people on the ground. Relevant Service Information We reviewed Boeing Service Bulletin 777–75A0002, Revision 1, dated October 26, 2011. This service information describes procedures for replacing bleed valve parts and tubing (including IP8 bleed valve ducts, duct bases, HP3 air tubes and associated parts) with new parts and tubing on the left and right Rolls-Royce RB211 Trent 800 engines. Boeing Service Bulletin 777– 75A0002, Revision 1, dated October 26, 2011, refers to Boeing Special Attention Service Bulletin 777–31–0177, dated September 23, 2010, as a concurrent requirement. This concurrent service bulletin describes procedures for installing the AEDB software, software part number 3110–BCG–00R–06, media set part number 243W0033–7, in the airplane AIMS hardware. Additionally, Boeing Service Bulletin 777–75A0002, Revision 1, dated October 26, 2011, refers to Rolls-Royce Service Bulletin RB.211–75–G466, dated June 20, 2011, as an additional source of guidance for replacing bleed valve parts and tubing. Other Relevant Rulemaking We issued AD 2005–07–24, Amendment 39–14049 (70 FR 18285, April 11, 2005), for Model 777–200 and –300 series airplanes equipped with Rolls-Royce Model RB211 TRENT 800 engines. That AD requires inspecting the thrust reversers for damage of the insulation blankets, the inner wall, and the compression and drag link fittings; and repair if necessary. That AD also requires applying sealant to certain areas of the thrust reverser. That AD refers to Boeing Alert Service Bulletin 777–78A0059, dated February 24, 2005, for doing the required actions. That AD was prompted by two reports of thrust reverser failure; investigation revealed that the inner wall of the thrust reversers had collapsed from exposure to hot engine core compartment air. We issued that AD to prevent failure of a thrust reverser and adjacent components and their consequent separation from the airplane, which could result in an RTO and cause asymmetric thrust and consequent loss of control of the airplane during reverse thrust operation. If an RTO does not occur, these separated components could cause structural damage to the airplane or damage to other airplanes and possible injury to people on the ground. 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 require accomplishing the actions specified in the Boeing service information described previously. 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 Parts cost Replacement ................................................... Installation of AEDB software ......................... 16 work-hours × $85 per hour = $1,360 ........ 1 work-hour × $85 per hour = $85 ................. 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. Authority for This Rulemaking mstockstill on DSK4VPTVN1PROD with PROPOSALS According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. We 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. 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 VerDate Mar<15>2010 15:54 Dec 09, 2011 Jkt 226001 Regulatory Findings For the reasons discussed above, I certify this 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 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 $75,000 0 Cost per product Cost on U.S. operators $76,360 85 $4,199,800 4,675 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. 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. E:\FR\FM\12DEP1.SGM 12DEP1 Federal Register / Vol. 76, No. 238 / Monday, December 12, 2011 / Proposed Rules § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA– 2011–1319; Directorate Identifier 2011– NM–143–AD. (a) Comments Due Date We must receive comments by January 26, 2012. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 777–200 and –300 series airplanes, certificated in any category, equipped with Rolls-Royce RB211 Trent 800 engines, as identified in Boeing Service Bulletin 777– 75A0002, Revision 1, dated October 26, 2011. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 78, Exhaust. (e) Unsafe Condition This AD was prompted by reports of events related to thermal damage of the thrust reverser (T/R) inner wall on Rolls-Royce RB211 Trent 800 engines. We are issuing this AD to eliminate T/R thermal damage caused by excessive heat downstream of the 8th stage IP8 exhaust ports, which could result in T/R structural failure. This failure could result in large pieces of the T/R or adjacent components departing the airplane. A separated T/R piece could result in a rejected takeoff and cause asymmetric thrust and consequent loss of control of the airplane during reverse thrust operations. Separated components could also cause structural damage to the airplane, damage to other airplanes, or injury to people on the ground. mstockstill on DSK4VPTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement of Bleed Valve Parts and Tubing Within 36 months after the effective date of this AD, replace the bleed valve parts and tubing with new parts and tubing on the left and right engines, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–75A0002, Revision 1, dated October 26, 2011. Note 1: The service bulletin accomplishment instructions might refer to other procedures. When the words ‘‘refer to’’ are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used to comply with the AD. When the words ‘‘in accordance with’’ are included in the instruction, the procedure in the design approval holder document must be used to comply with the AD. (h) Concurrent Requirements Prior to or concurrently with doing the actions required by paragraph (g) of this AD, VerDate Mar<15>2010 15:54 Dec 09, 2011 Jkt 226001 install Aero-Engine database software, software part number 3110–BCG–00R–06, media set part number 243W0033–7, in the airplane information management system hardware, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–31– 0177, dated September 23, 2010. (i) Maintenance (j) Credit for Actions Accomplished in Accordance With Previous Service Information Replacing the bleed valve parts and tubing with new parts and tubing on the left and right engines in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–75A0002, dated January 12, 2011, before the effective date of this AD is acceptable for compliance with the corresponding replacements required by paragraph (g) of this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be emailed to: 9–ANM– Seattle–ACO–AMOC–Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (l) Related Information (1) For more information about this AD, contact Rebel Nichols, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: (425) 917–6509; fax: (425) 917– 6590; email: Rebel.Nichols@faa.gov. (2) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; phone: (206) 544–5000, extension 1; fax: (206) 766–5680; email: me.boecom@boeing.com; Internet: https:// www.myboeingfleet.com. (3) For Rolls-Royce service information identified in this AD, contact Rolls-Royce plc, P.O. Box 31, DERBY, DE24 8BJ, UK; telephone 011 44 1332 242424; fax 011 44 1332 249936. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Frm 00003 Fmt 4702 Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call (425) 227–1221. Issued in Renton, Washington, on December 5, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–31738 Filed 12–9–11; 8:45 am] Note 2: After accomplishing the actions required by paragraphs (g) and (h) of this AD, maintenance and/or preventative maintenance under 14 CFR part 43 is permitted provided the maintenance does not result in changing the AD-mandated configuration (reference 14 CFR 39.7). PO 00000 77159 Sfmt 4702 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1318; Directorate Identifier 2010–NM–274–AD] RIN 2120–AA64 Airworthiness Directives; 328 Support Services GmbH Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 328 Support Services GmbH (Type Certificate previously held by AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328–100 and –300 airplanes that would supersede an existing AD. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: An incident has been reported with a Dornier 328–100 aeroplane, where the righthand (RH) power lever jammed in flight-idle position during the landing roll-out. The aeroplane was stopped by excessive braking. The reason for the jamming was that the cockpit door locking device * * * had fallen off the RH cockpit wall, blocking the RH power/condition lever pulley/cable cluster below the door. * * * This condition, if not corrected, could cause interference with the engine and/or flight control cables, possibly resulting in reduced control of the aeroplane. * * * * * The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by January 26, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. E:\FR\FM\12DEP1.SGM 12DEP1

Agencies

[Federal Register Volume 76, Number 238 (Monday, December 12, 2011)]
[Proposed Rules]
[Pages 77157-77159]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-31738]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 76, No. 238 / Monday, December 12, 2011 / 
Proposed Rules

[[Page 77157]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1319; Directorate Identifier 2011-NM-143-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 adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 777-200 and -300 series airplanes 
equipped with Rolls-Royce RB211 Trent 800 engines. This proposed AD was 
prompted by reports of events related to thermal damage of the thrust 
reverser (T/R) inner wall on Rolls-Royce RB211 Trent 800 engines. This 
proposed AD would require replacing the bleed valve parts and tubing 
with new parts and tubing on the left and right engines. Additionally, 
this proposed AD would require installing Aero-Engine database (AEDB) 
software in the airplane information management system (AIMS) hardware. 
We are proposing this AD to eliminate T/R thermal damage caused by 
excessive heat downstream of the 8th stage IP8 exhaust ports, which 
could result in T/R structural failure. This failure could result in 
large pieces of the T/R or adjacent components departing the airplane. 
A separated T/R piece could result in a rejected takeoff (RTO) and 
cause asymmetric thrust and consequent loss of control of the airplane 
during reverse thrust operations. Separated components could also cause 
structural damage to the airplane, damage to other airplanes, or injury 
to people on the ground.

DATES: We must receive comments on this proposed AD by January 26, 
2012.

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 Boeing service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; phone: (206) 
544-5000, extension 1; fax: (206) 766-5680; email: 
me.boecom@boeing.com; Internet: https://www.myboeingfleet.com. For 
Rolls-Royce service information identified in this AD, contact Rolls-
Royce plc, P.O. Box 31, DERBY, DE24 8BJ, UK; telephone 011 44 1332 
242424; fax 011 44 1332 249936. You may review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, Washington. For information on the 
availability of this material at the FAA, call (425) 227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at 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: Rebel Nichols, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 
(425) 917-6509; fax: (425) 917-6590; email: Rebel.Nichols@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2011-1319; 
Directorate Identifier 2011-NM-143-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

    We have received 14 reports of events related to thermal damage of 
the T/R inner wall on Rolls-Royce RB211 Trent 800 engines. The events 
have included air turnbacks, in-flight engine shutdowns, T/R inner wall 
panel sections and parts being separated from the airplane, collapse of 
the inner T/R inner wall panel, and engine fire loop fault messages.
    Boeing issued Alert Service Bulletin 777-78A0059, dated February 
24, 2005; and Special Attention Service Bulletin 777-78-0060, dated 
February 24, 2005; to provide instructions for inspecting the T/R inner 
wall panel structure and sealing the insulation blankets to prevent hot 
under-cowl air from contacting the T/R inner wall panel. Since those 
service bulletins were released, there have been four T/R events on 
airplanes on which those service bulletins had not been fully 
accomplished and 10 T/R events on airplanes on which those service 
bulletins had been accomplished.
    There are two separate causes of the thermal degradation. The first 
cause is the IP8 exhaust washing the outer side of the inner wall. This 
cause is addressed by this proposed AD through modification of the IP8 
bleed system. The second cause is the inadequate thermal protection 
system. We are considering further rulemaking to address this cause.

[[Page 77158]]

    This thermal degradation, if not corrected, could result in the T/R 
being damaged by excessive heat, which could result in thrust reverser 
structural failure. This failure could result in large pieces of the T/
R or adjacent components departing the airplane. A separated T/R piece 
could result in an RTO and cause asymmetric thrust and consequent loss 
of control of the airplane during reverse thrust operations. Separated 
components could also cause structural damage to the airplane, damage 
to other airplanes, or injury to people on the ground.

Relevant Service Information

    We reviewed Boeing Service Bulletin 777-75A0002, Revision 1, dated 
October 26, 2011. This service information describes procedures for 
replacing bleed valve parts and tubing (including IP8 bleed valve 
ducts, duct bases, HP3 air tubes and associated parts) with new parts 
and tubing on the left and right Rolls-Royce RB211 Trent 800 engines.
    Boeing Service Bulletin 777-75A0002, Revision 1, dated October 26, 
2011, refers to Boeing Special Attention Service Bulletin 777-31-0177, 
dated September 23, 2010, as a concurrent requirement. This concurrent 
service bulletin describes procedures for installing the AEDB software, 
software part number 3110-BCG-00R-06, media set part number 243W0033-7, 
in the airplane AIMS hardware.
    Additionally, Boeing Service Bulletin 777-75A0002, Revision 1, 
dated October 26, 2011, refers to Rolls-Royce Service Bulletin RB.211-
75-G466, dated June 20, 2011, as an additional source of guidance for 
replacing bleed valve parts and tubing.

Other Relevant Rulemaking

    We issued AD 2005-07-24, Amendment 39-14049 (70 FR 18285, April 11, 
2005), for Model 777-200 and -300 series airplanes equipped with Rolls-
Royce Model RB211 TRENT 800 engines. That AD requires inspecting the 
thrust reversers for damage of the insulation blankets, the inner wall, 
and the compression and drag link fittings; and repair if necessary. 
That AD also requires applying sealant to certain areas of the thrust 
reverser. That AD refers to Boeing Alert Service Bulletin 777-78A0059, 
dated February 24, 2005, for doing the required actions. That AD was 
prompted by two reports of thrust reverser failure; investigation 
revealed that the inner wall of the thrust reversers had collapsed from 
exposure to hot engine core compartment air. We issued that AD to 
prevent failure of a thrust reverser and adjacent components and their 
consequent separation from the airplane, which could result in an RTO 
and cause asymmetric thrust and consequent loss of control of the 
airplane during reverse thrust operation. If an RTO does not occur, 
these separated components could cause structural damage to the 
airplane or damage to other airplanes and possible injury to people on 
the ground.

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 require accomplishing the actions specified 
in the Boeing service information described previously.

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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replacement...........................  16 work-hours x $85 per          $75,000         $76,360      $4,199,800
                                         hour = $1,360.
Installation of AEDB software.........  1 work-hour x $85 per                  0              85           4,675
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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 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 this 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.

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.

[[Page 77159]]

Sec.  39.13  [Amended]

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

The Boeing Company: Docket No. FAA-2011-1319; Directorate Identifier 
2011-NM-143-AD.

(a) Comments Due Date

    We must receive comments by January 26, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -300 
series airplanes, certificated in any category, equipped with Rolls-
Royce RB211 Trent 800 engines, as identified in Boeing Service 
Bulletin 777-75A0002, Revision 1, dated October 26, 2011.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of events related to thermal 
damage of the thrust reverser (T/R) inner wall on Rolls-Royce RB211 
Trent 800 engines. We are issuing this AD to eliminate T/R thermal 
damage caused by excessive heat downstream of the 8th stage IP8 
exhaust ports, which could result in T/R structural failure. This 
failure could result in large pieces of the T/R or adjacent 
components departing the airplane. A separated T/R piece could 
result in a rejected takeoff and cause asymmetric thrust and 
consequent loss of control of the airplane during reverse thrust 
operations. Separated components could also cause structural damage 
to the airplane, damage to other airplanes, or injury to people on 
the ground.

(f) Compliance

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

(g) Replacement of Bleed Valve Parts and Tubing

    Within 36 months after the effective date of this AD, replace 
the bleed valve parts and tubing with new parts and tubing on the 
left and right engines, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 777-75A0002, Revision 1, 
dated October 26, 2011.

    Note 1: The service bulletin accomplishment instructions might 
refer to other procedures. When the words ``refer to'' are used and 
the operator has an accepted alternative procedure, the accepted 
alternative procedure can be used to comply with the AD. When the 
words ``in accordance with'' are included in the instruction, the 
procedure in the design approval holder document must be used to 
comply with the AD.

(h) Concurrent Requirements

    Prior to or concurrently with doing the actions required by 
paragraph (g) of this AD, install Aero-Engine database software, 
software part number 3110-BCG-00R-06, media set part number 
243W0033-7, in the airplane information management system hardware, 
in accordance with the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 777-31-0177, dated September 23, 2010.

(i) Maintenance

    Note 2:  After accomplishing the actions required by paragraphs 
(g) and (h) of this AD, maintenance and/or preventative maintenance 
under 14 CFR part 43 is permitted provided the maintenance does not 
result in changing the AD-mandated configuration (reference 14 CFR 
39.7).

(j) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    Replacing the bleed valve parts and tubing with new parts and 
tubing on the left and right engines in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
75A0002, dated January 12, 2011, before the effective date of this 
AD is acceptable for compliance with the corresponding replacements 
required by paragraph (g) of this AD.

(k) Alternative Methods of Compliance (AMOCs)

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

(l) Related Information

    (1) For more information about this AD, contact Rebel Nichols, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; phone: (425) 917-6509; fax: (425) 917-6590; 
email: Rebel.Nichols@faa.gov.
    (2) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; 
phone: (206) 544-5000, extension 1; fax: (206) 766-5680; email: 
me.boecom@boeing.com; Internet: https://www.myboeingfleet.com.
    (3) For Rolls-Royce service information identified in this AD, 
contact Rolls-Royce plc, P.O. Box 31, DERBY, DE24 8BJ, UK; telephone 
011 44 1332 242424; fax 011 44 1332 249936. You may review copies of 
the referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington. For 
information on the availability of this material at the FAA, call 
(425) 227-1221.

    Issued in Renton, Washington, on December 5, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-31738 Filed 12-9-11; 8:45 am]
BILLING CODE 4910-13-P

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