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[Federal Register Volume 79, Number 55 (Friday, March 21, 2014)]
[Rules and Regulations]
[Pages 15667-15671]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-06155]

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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; 
Amendment 39-17792; AD 2014-05-19]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting 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 AD was prompted by multiple reports 
of uncommanded thrust reverser unlock events. This AD requires 
replacing certain relays and relay sockets, and doing wiring changes. 
For certain airplanes, this AD also requires installing new relay 
panels, and removing and installing certain components. Additionally, 
this AD requires, for certain airplanes, accomplishing concurrent 
actions, which include installing an additional locking system on the 
thrust reversers and modifying system wiring for in-flight fault 
indications of the thrust reverser system. 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.

DATES: This AD is effective April 25, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of April 25, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
February 18, 2000 (65 FR 5222, February 3, 2000).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
September 14, 1994 (59 FR 41647, August 15, 1994).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; by searching for and locating Docket No. FAA-2013-
0331; or in person at the Docket

[[Page 15668]]

Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this AD, the regulatory 
evaluation, any comments received, and other information. The address 
for the Docket Office (phone: 800-647-5527) is Docket Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: 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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to 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. The NPRM published in the Federal Register on April 17, 2013 
(78 FR 22802). The NPRM was prompted by multiple reports of uncommanded 
thrust reverser unlock events. The NPRM proposed to require replacing 
certain relays and relay sockets, and doing wiring changes. For certain 
airplanes, the NPRM proposed to require installing new relay panels, 
and removing and installing certain components. Additionally, the NPRM 
proposed to 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 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(78 FR 22802, April 17, 2013) and the FAA's response to each comment.

Support for the NPRM (78 FR 22802, April 17, 2013)

    Boeing stated that it concurred with the contents of the NPRM (78 
FR 22802, April 17, 2013).
    The Air Line Pilots Association International stated that it agrees 
with the intent of the NPRM (78 FR 22802, April 17, 2013).

Request To Specify Thrust Reverser Unit (TRU) Part Numbers

    Rolls-Royce plc requested that instead of specifying the engine 
models, we specify the part numbers of the affected TRUs for tracking 
purposes. Rolls-Royce plc stated that the TRUs are swapped from engine 
to engine, and AD compliance would be difficult to track unless it is 
tracked based on the TRUs.
    We do not agree with the commenter's request. This final rule only 
requires changes to the control logic of the thrust reverser by 
modifying the associated electrical panels on the airplane. There is no 
requirement for TRU hardware replacement. Therefore, it is unnecessary 
to specify the part numbers of the affected TRUs in this final rule. We 
have not changed this final rule in this regard.

Statement of Financial Impact

    Rolls-Royce plc stated that it is likely the actions required by 
the NPRM (78 FR 22802, April 17, 2013) will have a significant 
financial affect upon Middle Eastern and Far East operations. Rolls-
Royce plc did not request any change to the NPRM in this regard.
    The commenter did not provide specific information to substantiate 
why Middle Eastern and Far East operations would be uniquely affected. 
The Costs of Compliance paragraph in this final rule is based on 
estimates provided in the service information and is an estimate of 
costs incurred by United States operators. We have not changed this 
final rule in this regard.

Changes to This Final Rule

    We clarified the required actions specified in the SUMMARY section 
of this final rule by removing the wording ``installing an additional 
locking system on the thrust reversers'' and ``installing a second 
locking gearbox system on the thrust reversers.'' These actions are 
included in the phrase ``installing an additional locking system on the 
thrust reversers.'' No change has been made to the actions required by 
this final rule.
    We revised paragraph (b) of this final rule to indicate that this 
final rule affects the requirements of AD 2000-01-05, Amendment 39-
11502 (65 FR 1051, January 7, 2000).
    We revised paragraph (h)(2) of this final rule to clarify that the 
installation of an additional gearbox is on the thrust reverser of each 
engine, rather than on each engine.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the change described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 22802, April 17, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 22802, April 17, 2013).

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                   Cost on U.S.
             Action                     Labor cost            Parts cost       Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Replacement and wiring change    30 work-hours x $85 per  $4,289............  $6,839............          $6,839
 for Model 747-200B, 747-200F,    hour = $2,550.
 747-300, and 747SP series
 airplanes (1 U.S.-registered
 airplane).

[[Page 15669]]

 
Removal, installations, and      Up to 90 work-hours x    Up to $16,607.....  Up to $24,257.....               0
 wiring changes for Model 747-    $85 per hour = $7,650.
 400 and 747-400F series
 airplanes (0 U.S.-registered
 airplanes).
Replacements and wiring changes  Up to 32 work-hours x    Up to $2,245......  Up to $4,965......               0
 for Model 767-300 series         $85 per hour = $2,720.
 airplanes (0 U.S.-registered
 airplanes).
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary concurrent 
requirements. We have no way of determining the number of aircraft that 
might need accomplishment of the concurrent requirements.

                                                Concurrent Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Installation of an additional locking        336 work-hours x $85 per hour =             $62,674         $91,234
 system for Model 747-200B, 747-200F, 747-    $28,560.
 300, and 747SP series airplanes.
Installation of an additional locking        185 work-hours x $85 per hour =              72,860          88,585
 gearbox on each engine and modification of   $15,725.
 the system wiring for Model 747-400 and
 747-400F series airplanes.
Installation of a second locking gearbox     754 work-hours x $85 per hour =                   0          64,090
 system for Model 767-300 series airplanes.   $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

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2014-05-19 The Boeing Company: Amendment 39-17792; Docket No. FAA-
2013-0331; Directorate Identifier 2011-NM-170-AD.

(a) Effective Date

    This AD is effective April 25, 2014.

(b) Affected ADs

    This AD affects the requirements of AD 2000-01-05, Amendment 39-
11502 (65 FR 1051, January 7, 2000).

(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, and 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 series airplanes, as identified 
in Boeing Service Bulletin 747-78-2180, Revision 2, dated November 
11, 2011.
    (3) Model 767-300 series airplanes, as identified in Boeing 
Service Bulletin 767-78-0096, Revision 1, dated December 10, 2009.

(d) Subject

    Joint Aircraft System/Component (JASC) Code 7830, Engine Thrust 
Reverser.

(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.

[[Page 15670]]

(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 the 
thrust reversers of 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, which is not incorporated by reference 
in this AD.
    (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, which is not incorporated by reference 
in this AD.
    (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, which is not incorporated 
by reference in this AD.
    (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, which is not incorporated by reference 
in this AD.
    (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, which was incorporated by reference in 
AD 99-18-03, Amendment 39-11269 (64 FR 47365, August 31, 1999).

    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, which is not incorporated 
by reference in this AD.

    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, which is not incorporated by 
reference in this AD, which was incorporated by reference in AD 94-
17-03, Amendment 39-8998 (59 FR 41647, August 15, 1994).

    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 paragraph (k) of this AD. Information may be 
emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
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) Service information identified in this AD that is not 
incorporated by reference may be obtained at the addresses specified 
in paragraphs (l)(6) and (l)(7) of this AD.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
April 25, 2014.
    (i) Boeing Service Bulletin 747-78-2156, Revision 1, dated 
August 30, 2001.

[[Page 15671]]

    (ii) Boeing Service Bulletin 747-78-2178, Revision 1, dated 
August 4, 2011.
    (iii) Boeing Service Bulletin 747-78-2180, Revision 2, dated 
November 11, 2011.
    (iv) Boeing Service Bulletin 767-78-0096, Revision 1, dated 
December 10, 2009.
    (4) The following service information was approved for IBR on 
February 18, 2000 (65 FR 5222, February 3, 2000).
    (i) Boeing Service Bulletin 747-78-2158, Revision 2, dated July 
29, 1999.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
September 14, 1994 (59 FR 41647, August 15, 1994).
    (i) Boeing Service Bulletin 767-78-0059, Revision 3, dated 
January 20, 1994.
    (ii) Reserved.
    (6) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet 
https://www.myboeingfleet.com.
    (7) You may view this service information at 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.
    (8) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 19, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-06155 Filed 3-20-14; 8:45 am]
BILLING CODE 4910-13-P
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