Document ID: FAA-2013-0331-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2013-04-17T04:00Z

[Federal Register Volume 78, Number 74 (Wednesday, April 17, 2013)]
[Proposed Rules]
[Pages 22802-22806]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-09006]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0331; Directorate Identifier 2011-NM-170-AD]
RIN 2120-AA64

Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 747-200B, 747-200F, 747-300, 747SP, 
747-400, and 747-400F series airplanes equipped with Rolls-Royce RB211-
524 engines; and certain Model 767-300 series airplanes equipped with 
Rolls-Royce RB211-524 engines. This proposed AD was prompted by 
multiple reports of uncommanded thrust reverser unlock events. This 
proposed AD would require replacing certain relays and relay sockets, 
and doing wiring changes. For certain airplanes, this proposed AD would 
also require installing new relay panels, and removing and installing 
certain components. Additionally, this proposed AD would require, for 
certain airplanes, accomplishing concurrent actions, which include 
installing an additional locking system on the thrust reversers, 
installing an additional locking gearbox on each engine and modifying 
system wiring for in-flight fault indications of the thrust reverser 
system, and installing a second locking gearbox system on the thrust 
reversers. We are proposing this AD to prevent an uncommanded thrust 
reverser deployment during takeoff or in-flight resulting in decreased 
airplane control and performance, possible runway excursions, and 
failure to climb.

DATES: We must receive comments on this proposed AD by June 3, 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 http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: 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 proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, P. 
O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; phone: 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 http://www.regulations.gov; or in person at the

[[Page 22803]]

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: Tung Tran, Aerospace Engineer, 
Propulsion Branch, ANM-140S, Seattle Aircraft Certification Office 
(ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-
917-6505; fax: 425-917-6590; email: Tung.Tran@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-2013-0331; 
Directorate Identifier 2011-NM-170-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 http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received multiple reports of uncommanded thrust reverser 
unlock events. In three of these events, all three thrust reverser 
locks had disengaged. One report stated that during takeoff roll on a 
Rolls-Royce RB211-524-powered Model 747-400 airplane, the flightcrew 
received the ENG 4 REV LIMTD EICAS status message and the ENG 4 
REVERSER advisory and status messages. During climb, the cabin crew saw 
sparks from the exhaust of the number 4 engine. The event was found to 
be caused by a failure of the o-rings in the air motor switcher or 
shutoff solenoid valves because of overheating. This let the air motor 
shutoff valve open, which released the air motor brake. Releasing the 
air motor brake in the ground mode energized the number 2 and number 3 
thrust reverser gear box unlock solenoids, thereby unlocking the number 
2 and number 3 gear boxes. The thrust reverser system on the Rolls-
Royce RB211-powered Model 767 airplane is similar to that on the Model 
747-400 airplane, and the Model 767 airplane thrust reverser system is 
likely to be susceptible to the same failure mode. This condition, if 
not corrected, could result an uncommanded thrust reverser deployment 
during takeoff or in-flight resulting in decreased airplane control and 
performance, possible runway excursions, and failure to climb.

Relevant Service Information

    We reviewed the following service information:
     Boeing Service Bulletin 747-78-2178, Revision 1, dated 
August 4, 2011.
     Boeing Service Bulletin 747-78-2180, Revision 2, dated 
November 11, 2011.
     Boeing Service Bulletin 767-78-0096, Revision 1, dated 
December 10, 2009.
    For information on the procedures and compliance times, see this 
service information at http://www.regulations.gov by searching for 
Docket No. FAA-2013-0331.

Concurrent Service Information

    Boeing Service Bulletin 747-78-2178, Revision 1, dated August 4, 
2011, specifies concurrent or prior accomplishment of Boeing Service 
Bulletin 747-78-2156, Revision 1, dated August 30, 2001. Boeing Service 
Bulletin 747-78-2180, Revision 2, dated November 11, 2011, specifies 
concurrent or prior accomplishment of Boeing Service Bulletin 747-78-
2158, Revision 2, dated July 29, 1999. Boeing Service Bulletin 767-78-
0096, Revision 1, dated December 10, 2009, specifies concurrent or 
prior accomplishment of Boeing Service Bulletin 767-78-0059, Revision 
3, dated January 20, 1994. For information on the procedures, see this 
service information at http://www.regulations.gov by searching for 
Docket No. FAA-2013-0331.

Other Relevant Rulemaking

    AD 2000-01-05, Amendment 39-11502 (65 FR 1051, January 7, 2000), 
which applies to certain Boeing Model 747-100B, -200, -300, and 747SP 
series airplanes equipped with Rolls-Royce RB211-524B2, C2, and D4 
engines, requires repetitive inspections and tests of the thrust 
reverser control and indication system on each engine, and corrective 
actions if necessary; installation of a terminating modification; and 
repetitive operational checks of that installation, and repair if 
necessary. AD 2000-01-05 refers to Boeing Service Bulletin 747-78-2156, 
dated October 31, 1996, as the appropriate source of service 
information for accomplishing the required terminating modification.
    AD 2000-02-22, Amendment 39-11540 (65 FR 5222, February 3, 2000), 
for certain Boeing Model 747-400 series airplanes equipped with Rolls-
Royce RB211-524G/H and RB211-524G-T/H-T engines, requires installation 
of a modification of the thrust reverser control and indication system 
and wiring on each engine; and repetitive operational checks of that 
installation to detect discrepancies, and repair if necessary. AD 2000-
02-22 refers to Boeing Service Bulletin 747-78-2158, Revision 2, dated 
July 29, 1999, as the appropriate source of service information for 
accomplishing the required modification.
    AD 94-17-03, Amendment 39-8998 (59 FR 41647, August 15, 1994), for 
certain Boeing Model 767 series airplanes equipped with Rolls-Royce 
RB211-524 series engines, requires inspections, adjustments, and 
functional checks of the thrust reverser system; installation of a 
terminating modification; and repetitive operational checks of the 
gearbox locks and the air motor brake following accomplishment of the 
modification. AD 94-17-03 refers to Boeing Service Bulletin 767-78-
0059, Revision 2, dated June 10, 1993; or Revision 3, dated January 20, 
1994; as the appropriate source of service information for 
accomplishing the required terminating action.

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 service information described previously.
    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.

[[Page 22804]]

Costs of Compliance

    We estimate that this proposed AD affects 1 airplane of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
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                                                                                                   Cost on U.S.
              Action                    Labor cost           Parts cost        Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Replacement and wiring change for  30 work-hours x $85  $4,289.............  $6,839.............          $6,839
 Model 747-200B, 747-200F, 747-     per hour = $2,550.
 300, and 747SP series airplanes
 (1 U.S. airplane).
Removal, installations, and        Up to 90 work-hours  Up to $16,607......  Up to $24,257......              $0
 wiring changes for Model 747-400   x $85 per hour =
 and 747-400F series airplanes (0   $7,650.
 U.S. airplanes).
Replacements and wiring changes    Up to 32 work-hours  Up to $2,245.......  Up to $4,965.......              $0
 for Model 767-300 series           x $85 per hour =
 airplanes (0 U.S. airplanes).      $2,720.
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    We estimate the following costs to do any necessary concurrent 
requirements. We have no way of determining the number of aircraft that 
might need to do the concurrent requirements.

                                                Concurrent Costs
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                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Installation of an additional locking system.  336 work-hours x $85 per hour =           $62,674         $91,234
                                                $28,560.
Installation of an additional locking gearbox  185 work-hours x $85 per hour =           $72,860         $88,585
 on each engine and modification of the         $15,725.
 system wiring.
Installation of a second locking gearbox       754 work-hours x $85 per hour =                $0         $64,090
 system.                                        $64,090.
----------------------------------------------------------------------------------------------------------------

 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

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):

The Boeing Company: Docket No. FAA-2013-0331; Directorate Identifier 
2011-NM-170-AD.

(a) Comments Due Date

    We must receive comments by June 3, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company airplanes, certificated in 
any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD, and equipped with Rolls-Royce RB211-524 engines.
    (1) Model 747-200B, 747-200F, 747-300, 747SP series airplanes, 
as identified in Boeing Service Bulletin 747-78-2178, Revision 1, 
dated August 4, 2011.
    (2) Model 747-400 and 747-400F airplanes, identified in Boeing 
Service Bulletin 747-78-2180, Revision 2, dated November 11, 2011.
    (3) Model 767-300 airplanes, as identified in Boeing Service 
Bulletin 767-78-0096, Revision 1, dated December 10, 2009.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 7830, Engine Thrust Reverser.

[[Page 22805]]

(e) Unsafe Condition

    This AD was prompted by multiple reports of uncommanded thrust 
reverser unlock events, three of which had all three locks 
disengaged. We are issuing this AD to prevent an uncommanded thrust 
reverser deployment during takeoff or in-flight resulting in 
decreased airplane control and performance, possible runway 
excursions, and failure to climb.

(f) Compliance

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

(g) Replacement

    Within 60 months after the effective date of this AD: Do the 
actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this 
AD, as applicable.
    (1) For Model 747-200B, 747-200F, 747-300, and 747SP series 
airplanes: Replace relays and relay sockets in the P252 and P253 
panels with new relays and relay sockets, and do wiring changes, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 747-78-2178, Revision 1, dated August 4, 2011.
    (2) For Model 747-400 and 747-400F series airplanes: Install the 
components removed from the existing P252 and P253 panels, install 
new relays and relay sockets, and do wiring changes on the new P252 
and P253 relay panels, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 747-78-2180, Revision 2, 
dated November 11, 2011.
    (3) For Model 767-300 series airplanes: Replace relays and relay 
sockets in the P36 and P37 panels with new relays and relay sockets, 
and do wiring changes in the P33, P36, and P37 panels, in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 767-
78-0096, Revision 1, dated December 10, 2009.

(h) Concurrent Requirements

    (1) For Model 747-200B, 747-200F, 747-300, and 747SP series 
airplanes: Prior to or concurrently with accomplishing the actions 
required by paragraph (g)(1) of this AD, install an additional 
locking system on the thrust reversers, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 747-78-2156, 
Revision 1, dated August 30, 2001. Accomplishing this installation 
is a method of compliance with the installation required by 
paragraph (c) of AD 2000-01-05, Amendment 39-11502 (65 FR 1051, 
January 7, 2000).
    (2) For Model 747-400 and 747-400F series airplanes identified 
as Group 1, 2, 3, 4, 7, 8, or 9 airplanes in Boeing Service Bulletin 
747-78-2180, Revision 2, dated November 11, 2011: Prior to or 
concurrently with accomplishing the actions required by paragraph 
(g)(2) of this AD, install an additional locking gearbox on each 
engine and modify system wiring for in-flight fault indications of 
the thrust reverser system, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 747-78-2158, Revision 2, 
dated July 29, 1999.

    Note 1 to paragraph (h)(2) of this AD: Paragraph (a)(1) of AD 
2000-02-22, Amendment 39-11540 (65 FR 5222, February 3, 2000), 
refers to Boeing Service Bulletin 747-78-2158, Revision 2, dated 
July 29, 1999, as the appropriate source of service information for 
accomplishing the installation required by that paragraph.

    (3) For Model 767-300 series airplanes identified as Group 2 
airplanes in Boeing Service Bulletin 767-78-0096, Revision 1, dated 
December 10, 2009: Prior to or concurrently with accomplishing the 
actions required by paragraph (g)(3) of this AD, install a second 
locking gearbox system on the thrust reversers, in accordance with 
the Accomplishment Instructions of Boeing Service Bulletin 767-78-
0059, Revision 3, dated January 20, 1994.

    Note 2 to paragraph (h)(3) of this AD: Paragraph (c) of AD 94-
17-03, Amendment 39-8998 (59 FR 41647, August 15, 1994), refers to 
Boeing Service Bulletin 767-78-0059, Revision 3, dated January 20, 
1994, as an appropriate source of service information for 
accomplishing the installation required by that paragraph.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for the requirements of 
paragraph (g)(1) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 747-78-
2178, dated January 22, 2009.
    (2) This paragraph provides credit for the requirements of 
paragraph (g)(2) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 747-78-
2180, dated April 10, 2008.
    (3) This paragraph provides credit for the requirements of 
paragraph (g)(2) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 747-78-
2180, Revision 1, dated November 11, 2010.
    (4) This paragraph provides credit for the requirements of 
paragraph (g)(3) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 767-78-
0096, dated August 7, 2008.
    (5) This paragraph provides credit for the requirements of 
paragraph (h)(1) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 747-78-
2156, dated October 31, 1996.

    Note 3 to paragraph (i)(5) of this AD: Paragraph (c) of AD 2000-
01-05, Amendment 39-11502 (65 FR 1051, January 7, 2000), refers to 
Boeing Service Bulletin 747-78-2156, dated October 31, 1996, as the 
appropriate source of service information for accomplishing the 
installation required by that paragraph.

    (6) This paragraph provides credit for the requirements of 
paragraph (h)(2) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 747-78-
2158, Revision 1, dated January 22, 1998.

    Note 4 to paragraph (i)(6) of this AD: In AD 2000-02-22, 
Amendment 39-11540 (65 FR 5222, February 3, 2000), Note 2 to 
paragraph (a)(1) of AD 2000-02-22 refers to Boeing Service Bulletin 
747-78-2158, Revision 1, dated January 22, 1998, as a method of 
compliance for accomplishing the installation required by paragraph 
(a)(1) of AD 2000-02-22.

    (7) This paragraph provides credit for the requirements of 
paragraph (h)(3) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Service Bulletin 767-78-
0059, Revision 2, dated June 10, 1993.

    Note 5 to paragraph (i)(7) of this AD: Paragraph (c) of AD 94-
17-03, Amendment 39-8998 (59 FR 41647, August 15, 1994), refers to 
Boeing Service Bulletin 767-78-0059, Revision 2, dated June 10, 
1993, as an appropriate source of service information for 
accomplishing the installation required by that paragraph.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office, 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.
    (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 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.

(k) Related Information

    (1) For more information about this AD, contact Tung Tran, 
Aerospace Engineer, Propulsion Branch, ANM-140S, Seattle Aircraft 
Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6505; fax: 425-917-6590; email: 
Tung.Tran@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; phone: 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, FAA, 
1601 Lind Avenue SW., Renton, WA. For information on the 
availability of this material at the FAA, call 425-227-1221.

[[Page 22806]]

    Issued in Renton, Washington, on April 10, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2013-09006 Filed 4-16-13; 8:45 am]
BILLING CODE 4910-13-P