[Federal Register Volume 78, Number 74 (Wednesday, April 17, 2013)]
[Proposed Rules]
[Pages 22802-22806]
From the Federal Register Online via the Government Publishing 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: [email protected].
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
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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
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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.
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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: [email protected].
(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:
[email protected].
(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]
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