Airworthiness Directives; The Boeing Company Airplanes, 15667-15671 [2014-06155]
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Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations
18, 2013; or Section 3.B. or 3.C. of RR Alert
NMSB No. RB.211–72–AG971, Revision 1,
dated September 27, 2013, to do the
inspection. Thereafter, inspect every 1,000
FC.
(iv) Perform an inspection of the top core
vanes, before exceeding 3,800 FCSN. Use
Section 3.C. of RR Alert NMSB No. RB.211–
72–AG971, Revision 1, dated September 27,
2013, to do the inspection. Thereafter,
inspect every 3,800 FC.
(2) If any inspection required by paragraph
(e)(1) of this AD fails, remove the TBH from
service.
(3) Remove any TBH from service before
the TBH exceeds 17,200 FCSN.
(f) Credit for Previous Actions
(1) If, before the effective date of this AD,
you performed inspections and corrective
actions using RR Alert NMSB No. RB.211–
72–AG971, dated September 20, 2012 or RR
Alert NMSB No. RB.211–72–AH154, dated
June 13, 2013; you met the requirements of
paragraph (e)(1) of this AD.
(2) If, before the effective date of this AD,
the last in-shop inspection of the mount lug
run-outs was accomplished using Section
3.C. of RR Alert NMSB No. RB.211–72–
AG971, dated September 20, 2012, the
compliance time interval for the next onwing or in-shop inspection of the fail safe
catcher, as required by paragraphs (e)(1)(ii)
and (e)(1)(iii) of this AD, may be counted
from that last in-shop inspection of the
mount lug run-outs.
(3) If, before the effective date of this AD,
you performed inspections and corrective
actions using RR Technical Variance (TV)
No. 124801, Issue 2, dated July 4, 2012 or
earlier versions; or TV No. 124851, Issue 2,
dated July 4, 2012 or earlier versions; you
met the requirements of paragraph (e)(1)(i) of
this AD.
(4) If, before the effective date of this AD,
you performed inspections and corrective
actions using RR TV No. 132043, Issue 1,
dated March 25, 2013 or earlier versions; or
TV No. 132217, Issue 5, dated May 23, 2013
or earlier versions; you met the requirements
of paragraphs (e)(1)(ii) and (e)(1)(iii) of this
AD.
(5) Any inspections and corrective actions
performed are not terminating action for the
repetitive inspections required by paragraph
(e)(1) of this AD.
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(g) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs to this AD. Use
the procedures found in 14 CFR 39.19 to
make your request.
(h) Related Information
(1) For more information about this AD,
contact Anthony W. Cerra, Jr., Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; phone: 781–238–7128; fax: 781–238–
7199; email: anthony.cerra@faa.gov.
(2) Refer to MCAI European Aviation
Safety Agency AD 2013–0240 (correction),
dated October 4, 2013, for more information.
You may examine the MCAI in the AD
docket on the Internet at https://
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15:59 Mar 20, 2014
Jkt 232001
www.regulations.gov by searching for and
locating it in Docket No. FAA–2013–1015.
(3) RR Repeater TV No. 132043, Repeater
TV No. 132217, TV No. 124801, and TV No.
124851, which are not incorporated by
reference in this AD, can be obtained from
RR, using the contact information in
paragraph (i)(3) of this AD.
(4) You may view this service information
at the FAA, Engine & Propeller Directorate,
12 New England Executive Park, Burlington,
MA. For information on the availability of
this material at the FAA, call 781–238–7125.
(i) 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.
(i) Rolls-Royce plc Alert Non-Modification
Service Bulletin (NMSB) No. RB.211–72–
AG971, Revision 1, dated September 27,
2013.
(ii) Rolls-Royce plc Alert NMSB No.
RB.211–72–AH154, Revision 1, dated June
18, 2013.
(3) For service information identified in
this AD, contact Rolls-Royce plc, Corporate
Communications, P.O. Box 31, Derby,
England, DE248BJ; phone: 011–44–1332–
242424; fax: 011–44–1332–245418, or email:
https://www.rolls-royce.com/contact/civil_
team.jsp.
(4) You may view this service information
at FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington,
MA. For information on the availability of
this material at the FAA, call 781–238–7125.
(5) You may view this service information
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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
February 27, 2014.
Colleen M. D’Alessandro,
Assistant Directorate Manager, Engine &
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2014–04952 Filed 3–20–14; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
AGENCY:
PO 00000
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ACTION:
15667
Final rule.
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 inflight 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.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; by searching for
and locating Docket No. FAA–2013–
0331; or in person at the Docket
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Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations
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. RollsRoyce 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
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Action
Labor cost
Parts cost
Cost per product
Replacement and wiring change for
Model 747–200B, 747–200F, 747–
300, and 747SP series airplanes (1
U.S.-registered airplane).
30 work-hours × $85 per hour = $2,550
$4,289 ....................
$6,839 ....................
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15:59 Mar 20, 2014
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Cost on U.S.
operators
$6,839
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Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations
ESTIMATED COSTS—Continued
Cost on U.S.
operators
Action
Labor cost
Parts cost
Cost per product
Removal, installations, and wiring
changes for Model 747–400 and 747–
400F series airplanes (0 U.S.-registered airplanes).
Replacements and wiring changes for
Model 767–300 series airplanes (0
U.S.-registered airplanes).
Up to 90 work-hours × $85 per hour =
$7,650.
Up to $16,607 ........
Up to $24,257 ........
0
Up to 32 work-hours × $85 per hour =
$2,720.
Up to $2,245 ..........
Up to $4,965 ..........
0
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
product
Action
Labor cost
Installation of an additional locking system for Model
747–200B, 747–200F, 747–300, and 747SP series
airplanes.
Installation of an additional locking gearbox on each
engine and modification of the system wiring for
Model 747–400 and 747–400F series airplanes.
Installation of a second locking gearbox system for
Model 767–300 series airplanes.
336 work-hours × $85 per hour = $28,560 ..................
$62,674
$91,234
185 work-hours × $85 per hour = $15,725 ..................
72,860
88,585
754 work-hours × $85 per hour = $64,090 ..................
0
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.
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Regulatory Findings
15:59 Mar 20, 2014
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
Jkt 232001
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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.
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(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 RollsRoyce 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
1. The authority citation for part 39
continues to read as follows:
■
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:
VerDate Mar<15>2010
(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.
Parts cost
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.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(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
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15:59 Mar 20, 2014
Jkt 232001
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
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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-AMOCRequests@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.
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21MRR1
Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–1023; Directorate
Identifier 2013–NM–042–AD; Amendment
39–17797; AD 2014–05–24]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
mstockstill on DSK4VPTVN1PROD with RULES
AGENCY:
We are superseding
Airworthiness Directive (AD) 84–19–01
for certain The Boeing Company Model
747–100, 747–200B, and 747–200F
series airplanes. AD 84–19–01 required
repetitive inspections for cracking of
certain tension ties, and repair and
SUMMARY:
VerDate Mar<15>2010
15:59 Mar 20, 2014
Jkt 232001
certain modifications if necessary. This
new AD requires, for certain airplanes,
additional inspections for cracking of
the tension tie at body station (BS) 760
or 780, corrective action if necessary,
and eventual modification of the tension
ties. For all airplanes, this new AD
requires repetitive post-modification
inspections for cracking of the tension
tie at BS 760 or 780, and corrective
action if necessary. This AD was
prompted by reports of cracking in the
BS 760 tension tie as a result of bending
due to cabin pressurization. We are
issuing this AD to detect and correct
tension tie cracking, which could
eventually result in in-flight
depressurization of the airplane and the
inability to withstand current regulatory
failsafe loads.
DATES: This AD is effective April 25,
2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 25, 2014.
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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2013–
1023; 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 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:
Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6428;
fax: 425–917–6590; email:
Nathan.P.Weigand@faa.gov.
PO 00000
Frm 00039
Fmt 4700
Sfmt 4700
15671
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 84–19–01,
Amendment 39–4913 (Docket No. 84–
NM–10–AD; 49 FR 36365, September
17, 1984). AD 84–19–01 applied to
certain Boeing Model 747–100, 747–
200B, and 747–200F series airplanes.
The NPRM published in the Federal
Register on December 6, 2013 (78 FR
73457). The NPRM was prompted by
reports of cracking in the BS 760 tension
tie as a result of bending due to cabin
pressurization. The NPRM proposed to
continue to require repetitive
inspections for cracking of certain
tension ties, and repair and certain
modifications if necessary. The NPRM
also proposed to require, for certain
airplanes, additional inspections for
cracking of the tension tie at BS 760 or
780, corrective action if necessary, and
eventual modification of the tension
ties. For all airplanes, the NPRM also
proposed to require repetitive postmodification inspections for cracking of
the tension tie at BS 760 or 780, and
corrective action if necessary. We are
issuing this AD to detect and correct
tension tie cracking, which could
eventually result in in-flight
depressurization of the airplane and the
inability to withstand current regulatory
failsafe loads.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
Boeing supported the NPRM (78 FR
73457, December 6, 2013).
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
73457, December 6, 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 73457,
December 6, 2013).
Costs of Compliance
We estimate that this AD affects 24
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
E:\FR\FM\21MRR1.SGM
21MRR1
]]>Agencies
[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://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: https://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
