Airworthiness Directives; The Boeing Company Airplanes, 17285-17290 [2013-05588]
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Rules and Regulations
Federal Register
Vol. 78, No. 55
Thursday, March 21, 2013
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22523; Directorate
Identifier 2005–NM–058–AD; Amendment
39–17379; AD 2013–05–07]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 767
airplanes. This AD was prompted by
reports of stiff operation of the elevator
pitch control system and jammed
elevator controls. This AD requires
replacing pressure seal assemblies;
doing repetitive inspections for dirt,
loose particles, or blockage of the
flanged tube and drain hole for the
pressure seals, and corrective action if
necessary; replacing the aft air-intake
duct assembly with a new or modified
assembly and installing a dripshield;
and installing gutters on the horizontal
stabilizer center section and modifying
the side brace fittings. We are issuing
this AD to prevent moisture from
collecting and freezing on the elevator
control system components, which
could limit the ability of the flightcrew
to make elevator control inputs and
result in reduced controllability of the
airplane.
This AD is effective April 25,
2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of April 25, 2013.
ADDRESSES: For service information
identified in this AD, contact Boeing
DATES:
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Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 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, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document 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:
Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: (425) 917–
6490; fax: (425) 917–6590; email:
Kelly.McGuckin@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to include an
airworthiness directive (AD) that would
apply to the specified products. That
SNPRM published in the Federal
Register on August 9, 2012 (77 FR
47563). The original NPRM (70 FR
56386, September 27, 2005) proposed to
require drilling a drain hole in the
flanged tubes for certain elevator control
cable aft pressure seals; doing repetitive
inspections for dirt, loose particles, or
blockage of the flanged tube and drain
hole for the pressure seals, and
corrective action if necessary; replacing
the aft air-intake duct assembly with a
new or modified assembly and
installing a dripshield; and installing
gutters on the horizontal stabilizer
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center section and modifying the side
brace fittings. The SNPRM proposed to
revise the NPRM by requiring
replacement of pressure seal assemblies,
rather than the proposed drilling of
drain holes; revising a certain
compliance time and inspection type;
adding certain optional actions; and
revising the applicability.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the SNPRM (77 FR 47563,
August 9, 2012) and the FAA’s response
to each comment. One commenter,
Natalia Budyldina, stated the SNPRM is
significant since it is related to airplane
safety, would let the pilot better control
the airplane, and would reduce airplane
delays due to technical problems.
Request To Allow Installing New or
Modified Aft Air-Intake Duct
Assemblies
UPS requested that we revise
paragraph (i) of the SNPRM (77 FR
47563, August 9, 2012) to clarify if
operators are allowed to install a ‘‘new
or reworked duct’’ on all affected
airplanes or if operators must strictly
follow the service information. UPS
stated that paragraph (i) of the SNPRM
requires installation of a ‘‘new or
modified’’ aft air-intake duct assembly
in accordance with Boeing Service
Bulletin 767–49A0035, Revision 2,
dated June 2, 2006, which specifies to
install a new duct assembly on the first
airplane modified in an operator’s fleet
and to install reworked duct assemblies
on the operator’s remaining fleet.
We agree that installing either new or
reworked duct assemblies on all
airplanes in an operator’s fleet addresses
the identified unsafe condition. We
have revised paragraph (i) of this AD to
refer to new paragraph (k)(8) of this AD,
which states that where Boeing Service
Bulletin 767–49A0035, Revision 2,
dated June 2, 2006, specifies installing
a new aft air-intake duct assembly on
the first airplane in each operator’s fleet
and installing a reworked aft air-intake
duct assembly on all remaining
airplanes in each operator’s fleet, this
AD requires installing either a new or
reworked aft air-intake duct assembly
on all airplanes.
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Request To Extend Compliance Time
Boeing requested that, for airplanes
on which Boeing Service Bulletin 767–
27A0219 has been done, we extend the
compliance time specified in paragraph
(g)(1)(ii) of the SNPRM (77 FR 47563,
August 9, 2012) from 6 months to 24
months after the effective date of the AD
for the inspections specified in Boeing
Service Bulletin 767–27–0204, Revision
2, dated August 16, 2011; and Boeing
Service Bulletin 767–27–0205, Revision
2, dated August 30, 2011. Boeing stated
that the 24-month compliance time,
which will allow operators to
incorporate the drain hole inspection
into a standard maintenance interval, is
supported by the Boeing analysis in
which the compliance recommendation
for Boeing Service Bulletin 767–27–
0204, Revision 2, dated August 16,
2011; and Boeing Service Bulletin 767–
27–0205, Revision 2, dated August 30,
2011, was formulated.
We agree. We have determined that,
for airplanes on which Boeing Service
Bulletin 767–27A0219 has been done as
of the effective date of this AD, a
compliance time of within 24 months
will provide an acceptable level of
safety for accomplishing the inspection
required by paragraph (g) of this AD. We
have revised paragraph (g)(1) of this AD
accordingly (and removed paragraphs
(g)(1)(i) and (g)(1)(ii) of the SNPRM (77
FR 47563, August 9, 2012)).
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Request To Add Exception for Group 4
Airplanes Identified in Boeing Service
Bulletin 767–27A0224, Revision 1,
Dated December 16, 2011
Boeing requested that we add an
exception for Group 4 airplanes
identified in Boeing Service Bulletin
767–27A0224, Revision 1, dated
December 16, 2011, to allow operators
that have replaced the configuration
having two seal plates (part numbers
(P/Ns) 255T4847–1 and 65–28174–1)
with the configuration having one seal
plate (P/N 255T4847–5) to omit the
removal/installation of the kept part,
named ‘‘SEAL PLATE ASSEMBLY,’’
while performing Figures 7 through 10
of Boeing Service Bulletin 767–
27A0224, Revision 1, dated December
16, 2011. Boeing also stated that Group
1 though 3 airplanes can use the twopart configuration as an alternative to
the one-part configuration while
performing Figure 1 and Figures 4
through 6 of Boeing Service Bulletin
767–27A0224, Revision 1, dated
December 16, 2011. Boeing stated the
installation of P/N 255T4847–5 is
equivalent to the combination of P/Ns
255T4847–1 and 65–28174–1 for the
purposes of Boeing Service Bulletin
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767–27A0224, Revision 1, dated
December 16, 2011.
We agree to add an exception to this
AD, for the reasons provided by the
commenter. We have revised paragraphs
(h) and (l) of this AD to refer to new
paragraphs (k)(9) and (k)(10) of this AD:
• Paragraph (k)(9) of this AD
specifies, for Group 4 airplanes, as
identified in Boeing Service Bulletin
767–27A0224, Revision 1, dated
December 16, 2011, that where Figures
7 through 10 of Boeing Service Bulletin
767–27A0224, Revision 1, dated
December 16, 2011, specify to replace
the seal plate assembly, this AD allows
replacing the configuration having two
seal plates, P/Ns 255T4847–1 and 65–
28174–1, with the configuration having
one seal plate, P/N 255T4847–5.
• Paragraph (k)(10) to this AD
specifies, for Group 1 through 3
airplanes, as identified in Boeing
Service Bulletin 767–27A0224, Revision
1, dated December 16, 2011, that where
Figures 1 and Figures 4 through 6 of
Boeing Service Bulletin 767–27A0224,
Revision 1, dated December 16, 2011,
specify to replace the seal plate, this AD
allows replacing the configuration
having one seal plate, P/N 255T4847–5,
with the configuration having two seal
plates, P/Ns 255T4847–1 and 65–
28174–1.
Request for Exception To Allow
Installation of Clamp
Boeing requested that we allow
installation of a clamp, P/N AN735–( ),
having a larger diameter than the clamp
specified in steps 8 and 9 of Figure 4
and steps 8 and 9 of Figure 8 of Boeing
Service Bulletin 767–27A0224, Revision
1, dated December 16, 2011. Boeing
stated that the existing flanged tube may
have a repair that increases its diameter
and that installation of a clamp, P/N
AN735–( ), of increased diameter would
be necessary in order to meet the clamp
installation specifications.
We agree to allow installation of the
larger clamps, P/N AN735–( ), as
requested. We have revised paragraphs
(h) and (l) to refer to new paragraph
(k)(11) of this AD, which specifies that
where steps 8 and 9 of Figure 4 and
steps 8 and 9 of Figure 8 of Boeing
Service Bulletin 767–27A0224, Revision
1, dated December 16, 2011, specify
installing clamp P/N AN735–16, this
AD allows, for airplanes having
increased diameter of the flanged tube
due to a repair, installation of a clamp,
P/N AN735–( ), that has a larger
diameter than P/N AN735–16.
Request To Allow Substitute Fasteners
Boeing requested that we allow
substitute fasteners (bolts) for the bolts
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specified in Figures 6 and 10 of Boeing
Service Bulletin 767–27A0224, Revision
1, dated December 16, 2011. Boeing
stated that bolts, P/N BACB30NT3K( ),
BACB30LK3–( ), BACB30ZG3–( ), and
NAS623–3–( ), are substitutes for the
bolts specified in steps 1 and 4 of Figure
6 and steps 1 and 4 of Figure 10 of
Boeing Service Bulletin 767–27A0224,
Revision 1, dated December 16, 2011.
Boeing stated that airplanes were
delivered with those other equivalent
part numbers and that the structural
repair manual may not specify that
these bolts are acceptable substitutes.
We agree to add an exception to this
AD for the reason provided by the
commenter. We have revised paragraphs
(h) and (l) to refer to new paragraph
(k)(12) of this AD, which specifies that
where steps 1 and 4 of Figure 6 and
steps 1 and 4 of Figure 10 of Boeing
Service Bulletin 767–27A0224, Revision
1, dated December 16, 2011, specify
installing bolts, this AD allows
installation of bolts having P/N
BACB30NT3K( ), BACB30LK3–( ),
BACB30ZG3–( ), or NAS623–3–( ).
Request To Allow Exception for
Operators That Have Done a
Replacement
Boeing requested that we add an
exception for airplanes identified as
Group 1, Configuration 2 through 4
airplanes, Group 2 and 3 airplanes, and
Group 4, Configuration 2 through 4
airplanes, in Boeing Service Bulletin
767–27A0224, Revision 1, dated
December 16, 2011 (we referred to that
service bulletin as the appropriate
source of service information for
accomplishing the replacement required
by paragraph (h) of the SNPRM (77 FR
47563, August 9, 2012), and the optional
replacement specified in paragraph (l) of
the SNPRM). Boeing stated the
exception would allow operators that
replaced a flanged tube with a new
flanged tube as a repair (after
accomplishing Boeing Service Bulletin
767–27A0224, Revision 1, dated
December 16, 2011) to install the
replacement flanged tube without
restoring the drain hole and clamp.
Boeing stated that replacement flanged
tubes do not have a pre-drilled drain
hole, and it is unnecessary to restore the
configuration with the drain hole and
clamp to cover the drain hole.
We disagree with the request to add
an exception to this AD for operators
that have accomplished the replacement
specified in paragraph (h) or (l) of this
AD. Boeing did not submit information
(e.g., what specific replacement parts
are acceptable) to substantiate that this
method of compliance with paragraphs
(h) and (l) of this AD addresses the
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identified unsafe condition. Once we
issue this AD, any person may request
approval of an AMOC under the
provisions of paragraph (n) of this AD.
We have not changed this AD in this
regard.
Request To Confirm Credit for a Certain
Boeing Service Bulletin
United Airlines requested we confirm
that credit is provided for previous
accomplishment of Boeing Service
Bulletin 767–51A0027, Revision 1,
dated October 12, 2006. United Airlines
noted that paragraph (m)(4) of the
SNPRM (77 FR 47563, August 9, 2012)
provides credit for Boeing Alert Service
Bulletin 767–51A0027, dated December
9, 2004.
We agree to clarify. This AD does
provide credit for previous
accomplishment (i.e., before the
effective date of this AD) of Boeing
Service Bulletin 767–51A0027, Revision
1, dated October 12, 2006 (the
appropriate source of service
information for certain Model 767–200,
–300, and –300F series airplanes for
accomplishing the actions required by
paragraph (j) of this AD). Paragraph (f)
of this AD states: ‘‘Comply with this AD
within the compliance times specified,
unless already done.’’ The intent of
paragraph (f) of this AD is to allow
credit for previous accomplishment of
the service information required by the
AD.
For previous issues of required
service information, each AD specifies
in a separate paragraph whether credit
is given for those previous issues.
Paragraph (m)(4) of this AD provides
credit for Boeing Alert Service Bulletin
767–51A0027, dated December 9, 2004,
which is the previous issue of the
required service bulletin, Boeing Service
Bulletin 767–51A0027, Revision 1,
dated October 12, 2006. We have not
changed this AD in this regard.
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Request To Clarify Paragraphs (g) and
(h) of the SNPRM (77 FR 47563, August
9, 2012)
UPS requested that we clarify the
requirements of paragraphs (g) and (h)
of the SNPRM (77 FR 47563, August 9,
2012). UPS stated that paragraph (g) of
the SNPRM requires inspections in
accordance with the work instructions
contained in Boeing Service Bulletin
767–27–0204, Revision 2, dated August
16, 2011, and that Boeing Service
Bulletin 767–27–0204, Revision 2, dated
August 16, 2011, lists Boeing Service
Bulletin 767–27A0219, Revision 1,
dated February 12, 2009, as a
‘‘concurrent requirement.’’ UPS asked if
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the intent of paragraph (g) of the
SNPRM is to mandate the inspections
without the ‘‘concurrent requirement’’
of the modification specified in Boeing
Service Bulletin 767–27A0219, Revision
1, dated February 12, 2009. UPS stated
that if the intent is to require the
inspections and the modifications, then
paragraph (h) of the SNPRM should
read: ‘‘Accomplishing this replacement
terminates the inspections and
modification required by paragraph (g)
of this AD.’’
We agree to clarify. Paragraph (g) of
this AD requires that inspections
specified in Boeing Service Bulletin
767–27–0204, Revision 2, dated August
16, 2011, be done. The compliance time
for doing those inspections is dependent
on whether or not any revision of
‘‘Boeing Service Bulletin 767–27A0219’’
has been done, as specified in
paragraphs (g)(1) and (g)(2) of this AD;
however, paragraph (g) of this AD does
not require that the modification
specified in Boeing Service Bulletin
767–27A0219, Revision 1, dated
February 12, 2009, must be done. We
have not changed this AD in this regard.
Request for Flexibility in Use of
Abrasive
UPS requested that we allow
flexibility in the use of abrasive
specified in Figure 5 of Boeing Service
Bulletin 767–27A0224, Revision 1,
dated December 16, 2011. UPS stated
that paragraph (h) of the SNPRM (77 FR
47563, August 9, 2012) would require
accomplishment of that service bulletin.
(Paragraph (l) of the SNPRM would also
require that service bulletin, if the
actions in paragraph (l) of the SNPRM
are done.) UPS stated that Figure 5
specifies to use an abrasive to prepare
for adhesive application and that ‘‘80grit is recommended.’’ UPS also noted
that Figure 5 refers to standard overhaul
practices manual (SOPM) 20–50–12 for
adhesive mixing and surface cleaning.
UPS asked if operators are allowed the
flexibility offered by the SOPM.
We agree that there is flexibility in the
use of abrasive specified in Figure 5 of
Boeing Service Bulletin 767–27A0224,
Revision 1, dated December 16, 2011.
There is no requirement in this AD that
mandates the use of 80-grit abrasive. As
noted by the commenter, Figure 5 of
Boeing Service Bulletin 767–27A0224,
Revision 1, dated December 16, 2011,
only recommends the use of 80-grit
abrasive and includes a reference to
SOPM 20–50–12. Similarly, Figures 4, 8,
and 9 of Boeing Service Bulletin 767–
27A0224, Revision 1, dated December
16, 2011, only recommend the use of 80-
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grit abrasive. Operators may use an
abrasive of the specific grit referenced in
SOPM 20–50–12 to accomplish the
actions specified in steps 1 and 2 of
Figures 4, 5, 8, and 9 of Boeing Service
Bulletin 767–27A0224, Revision 1,
dated December 16, 2011. We have not
changed this AD in this regard.
Request To Revise Effectivity Listed in
the Preamble of the SNPRM (77 FR
47563, August 9, 2012)
Boeing requested that we revise the
effectivity for Boeing Service Bulletin
767–27–0204, Revision 2, dated August
16, 2011, specified in the ‘‘Actions
Since Previous NPRM (70 FR 56386,
September 27, 2005) was Issued’’
section of the preamble of the SNPRM
(77 FR 47563, August 9, 2012). Boeing
stated that the effectivity listed in the
SNPRM should be revised to include
line numbers 972 through 974 to match
the effectivity listed in Boeing Service
Bulletin 767–27–0204, Revision 2, dated
August 16, 2011.
We acknowledge that the effectivity of
Boeing Service Bulletin 767–27–0204,
Revision 2, dated August 16, 2011, is
line numbers 225, 226, 228 through 717,
and 719 through 971, except airborne
warning and control system (AWACS)
airplanes; and line numbers 972 through
974. However, the ‘‘Actions Since
Previous NPRM (70 FR 56386,
September 27, 2005) was Issued’’
section of the SNPRM (77 FR 47563,
August 9, 2012) is not restated in this
AD. We have not changed this AD in
this regard.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously—
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the SNPRM (77 FR
47563, August 9, 2012) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM (77 FR 47563,
August 9, 2012).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of the AD.
Costs of Compliance
We estimate that this AD affects about
400 airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Inspection of the flanged tube
and drain hole (300 airplanes).
Pressure seal replacement
(300 airplanes).
Aft air-intake duct assembly
replacement and dripshield
installation (358 airplanes).
Horizontal stabilizer gutter installation and modification
of the side brace fittings
(354 airplanes).
Cost per product
Cost on U.S.
operators
$0
$170 per inspection cycle ......
$51,000 per inspection cycle.
261
$856 .......................................
$256,800.
1,462
$1,717 ....................................
$614,686.
1,902
$2,922 ....................................
$1,034,388.
Parts cost
2 work-hours × $85 per hour
= $170 per inspection cycle.
7 work-hours × $85 per hour
= $595.
3 work-hours × $85 per hour
= $255.
12 work-hours × $85 per hour
= $1,020.
We estimate the following costs to do
any necessary cleaning that would be
required based on the results of the
inspection. We have no way of
determining the number of aircraft that
might need this cleaning.
ON-CONDITION COSTS
Action
Labor cost
Cleaning ............................
1 work-hour × $85 per hour = $85 ...........................................................................
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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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,
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14:39 Mar 20, 2013
(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
1. The authority citation for part 39
continues to read as follows:
■
Regulatory Findings
Jkt 229001
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):
■
2013–05–07 The Boeing Company:
Amendment 39–17379; Docket No.
FAA–2005–22523; Directorate Identifier
2005–NM–058–AD.
(a) Effective Date
This AD is effective April 25, 2013.
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Cost per
product
Parts cost
$0
$85
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 767–200, –300, –300F, and –400ER
series airplanes, certificated in any category;
as identified in the service information
specified in paragraphs (c)(1), (c)(2), (c)(3),
(c)(4), (c)(5), and (c)(6) of this AD.
(1) Boeing Service Bulletin 767–27A0224,
Revision 1, dated December 16, 2011.
(2) Boeing Service Bulletin 767–49A0035,
Revision 2, dated June 2, 2006.
(3) Boeing Service Bulletin 767–27–0204,
Revision 2, dated August 16, 2011.
(4) Boeing Service Bulletin 767–27–0205,
Revision 2, dated August 30, 2011.
(5) Boeing Service Bulletins 767–51A0027,
Revision 1, dated October 12, 2006.
(6) Boeing Service Bulletin 767–51A0028,
Revision 1, dated October 12, 2006.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 27, Flight controls; 49, Airborne
auxiliary power; and 51, Standard practices/
structures.
(e) Unsafe Condition
This AD was prompted by reports of stiff
operation of the elevator pitch control system
and jammed elevator controls. We are issuing
this AD to prevent moisture from collecting
and freezing on the elevator control system
components, which could limit the ability of
the flightcrew to make elevator control inputs
and result in reduced controllability of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Inspections and Corrective Actions
For airplanes identified in Boeing Service
Bulletin 767–27–0204, Revision 2, dated
August 16, 2011; and Boeing Service Bulletin
767–27–0205, Revision 2, dated August 30,
2011: At the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD, do a
general visual inspection for dirt, loose
particles, and blockage of the flanged tube
and drain hole for the E1A and E1B elevator
control cable aft pressure seals, and all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 767–27–0204,
Revision 2, dated August 16, 2011 (for Model
767–200, –300, and –300F series airplanes);
or Boeing Service Bulletin 767–27–0205,
Revision 2, dated August 30, 2011 (for Model
767–400ER series airplanes). Do all
applicable corrective actions before further
flight. Repeat the inspection thereafter at
intervals not to exceed 24 months.
(1) For airplanes on which Boeing Service
Bulletin 767–27A0219 has been done as of
the effective date of this AD: Within 24
months after the effective date of this AD.
(2) For airplanes on which Boeing Service
Bulletin 767–27A0219 has not been done as
of the effective date of this AD: Do the
inspection at the time specified in paragraph
(g)(2)(i) or (g)(2)(ii) of this AD, whichever
occurs later.
(i) Within 24 months after the effective
date of this AD.
(ii) Within 24 months since the date of
issuance of the original airworthiness
certificate or the date of issuance of the
original export certificate of airworthiness.
wreier-aviles on DSK5TPTVN1PROD with RULES
(h) Replacement—Pressure Seal Assemblies
For Group 1, Configuration 1 and 2
airplanes; Group 2, Configuration 1 airplanes;
and Group 4, Configuration 1 and 2
airplanes; as identified in Boeing Service
Bulletin 767–27A0224, Revision 1, dated
December 16, 2011: Within 24 months after
the effective date of this AD, replace the two
existing pressure seal assemblies for the left
elevator control cables at the aft pressure
bulkhead, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 767–27A0224, Revision 1,
dated December 16, 2011, except as provided
by paragraphs (k)(9), (k)(10), (k)(11), and
(k)(12) of this AD. Accomplishing this
replacement terminates the inspections
required by paragraph (g) of this AD.
(i) Replacement—Air-Intake Duct Assembly
and Installation—Dripshield
For airplanes identified in Boeing Service
Bulletin 767–49A0035, Revision 2, dated
June 2, 2006: Within 18 months after the
effective date of this AD, replace the aft airintake duct assembly with a new or modified
aft air-intake duct assembly and install a
dripshield, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 767–49A0035, Revision 2,
dated June 2, 2006, except as provided by
paragraphs (k)(1) and (k)(8) of this AD.
(j) Gutter Installation and Side Brace
Modification
For airplanes identified in Boeing Service
Bulletin 767–51A0027, Revision 1, dated
VerDate Mar<14>2013
14:39 Mar 20, 2013
Jkt 229001
October 12, 2006; and Boeing Service
Bulletin 767–51A0028, Revision 1, dated
October 12, 2006: Within 60 months after the
effective date of this AD, install gutters on
the horizontal stabilizer center section, and
modify the side brace fittings, including
doing a dye penetrant or high frequency eddy
current inspection for cracking and damage
of the drain hole and all applicable corrective
actions, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 767–51A0027, Revision 1,
dated October 12, 2006 (for Model 767–200,
–300, and –300F series airplanes); or Boeing
Service Bulletin 767–51A0028, Revision 1,
dated October 12, 2006 (for Model 767–
400ER series airplanes); except as provided
by paragraphs (k)(2), (k)(3), (k)(4), (k)(5),
(k)(6), and (k)(7) of this AD.
(k) Exceptions to Service Information
(1) Where step 1 of Figure 4 of Boeing
Service Bulletin 767–49A0035, Revision 2,
dated June 2, 2006, specifies installing the
forward air-intake duct, that installation is
not required by this AD.
(2) Where Boeing Service Bulletin 767–
51A0027, Revision 1, dated October 12, 2006;
and Boeing Service Bulletin 767–51A0028,
Revision 1, dated October 12, 2006; specify
to contact Boeing for appropriate action:
Before further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (n) of this AD.
(3) Where step 8 in Figures 6 and 10 of
Boeing Service Bulletin 767–51A0027,
Revision 1, dated October 12, 2006; and
Boeing Service Bulletin 767–51A0028,
Revision 1, dated October 12, 2006; specify
hydraulic hose, part number (P/N) AS115–
08D0274, the correct part number is AS115–
08D0280.
(4) For steps 4, 8, and 12 in Figures 6 and
10 of Boeing Service Bulletin 767–51A0027,
Revision 1, dated October 12, 2006; and
Boeing Service Bulletin 767–51A0028,
Revision 1, dated October 12, 2006:
Hydraulic hose, P/N AS115–08K0280, is an
option to P/N AS115–08D0280.
(5) For steps 2, 6, and 10 in Figures 6 and
10 of Boeing Service Bulletin 767–51A0027,
Revision 1, dated October 12, 2006; and
Boeing Service Bulletin 767–51A0028,
Revision 1, dated October 12, 2006:
Hydraulic hose, P/N AS115–06K0274, is an
option to P/N AS115–06D0274.
(6) Steps 3.B.16 and 3.B.17 of Boeing
Service Bulletin 767–51A0027, Revision 1,
dated October 12, 2006; and Boeing Service
Bulletin 767–51A0028, Revision 1, dated
October 12, 2006; are not required by this
AD.
(7) Where note (d) of Figure 8 of Boeing
Service Bulletin 767–51A0027, Revision 1,
dated October 12, 2006; and Boeing Service
Bulletin 767–51A0028, Revision 1, dated
October 12, 2006; specifies to ‘‘install collars
on the upper surface of the gutter,’’ this AD
requires that operators install these bolts
with the bolt heads either up or down
provided that the bolt head direction
prevents interference between the collars and
the hydraulic lines.
(8) Where Boeing Service Bulletin 767–
49A0035, Revision 2, dated June 2, 2006,
specifies installing a new aft air-intake duct
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
17289
assembly on the first airplane in each
operator’s fleet and installing a reworked aft
air-intake duct assembly on all remaining
airplanes in each operator’s fleet, this AD
requires installing either a new or reworked
aft air-intake duct assembly on all airplanes.
(9) For Group 4 airplanes, as identified in
Boeing Service Bulletin 767–27A0224,
Revision 1, dated December 16, 2011: Where
Figures 7 through 10 of Boeing Service
Bulletin 767–27A0224, Revision 1, dated
December 16, 2011, specify to replace the
seal plate assembly, this AD allows replacing
the configuration having two seal plates, P/
Ns 255T4847–1 and 65–28174–1, with the
configuration having one seal plate, P/N
255T4847–5.
(10) For Group 1 through 3 airplanes, as
identified in Boeing Service Bulletin 767–
27A0224, Revision 1, dated December 16,
2011: Where Figures 1 and Figures 4 through
6 of Boeing Service Bulletin 767–27A0224,
Revision 1, dated December 16, 2011, specify
to replace the seal plate, this AD allows
replacing the configuration having one seal
plate, P/N 255T4847–5 with the
configuration having two seal plates, P/Ns
255T4847–1 and 65–28174–1.
(11) Where steps 8 and 9 of Figure 4 and
steps 8 and 9 of Figure 8 of Boeing Service
Bulletin 767–27A0224, Revision 1, dated
December 16, 2011, specify installing clamp
P/N AN735–16, this AD allows, for airplanes
having increased diameter of the flanged tube
due to a repair, installation of a clamp, P/N
AN735–( ), that has a larger diameter than P/
N AN735–16.
(12) Where steps 1 and 4 of Figure 6 and
steps 1 and 4 of Figure 10 of Boeing Service
Bulletin 767–27A0224, Revision 1, dated
December 16, 2011, specify installing bolts,
this AD allows installation of bolts having P/
N BACB30NT3K( ), BACB30LK3–( ),
BACB30ZG3–( ), or NAS623–3–( ).
(l) Optional Replacement—Pressure Seal
Assemblies
For Group 1, Configuration 3 and 4
airplanes; Group 2, Configuration 2 and 3
airplanes; Group 3 airplanes; and Group 4,
Configuration 3 and 4 airplanes; as identified
in Boeing Service Bulletin 767–27A0224,
Revision 1, dated December 16, 2011:
Replacing the two existing pressure seal
assemblies for the left elevator control cables
at the aft pressure bulkhead, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 767–27A0224,
Revision 1, dated December 16, 2011, except
as provided by paragraphs (k)(9), (k)(10),
(k)(11), and (k)(12) of this AD, terminates the
inspections required by paragraph (g) of this
AD.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if the actions were performed before the
effective date of this AD using the applicable
service information in paragraph (m)(1)(i) or
(m)(1)(ii) of this AD, which are not
incorporated by reference.
(i) For Model 767–200, –300, and –300F
series airplanes: Boeing Service Bulletin 767–
27–0204, dated January 27, 2005; or Boeing
Service Bulletin 767–27–0204, Revision 1,
dated February 12, 2009.
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Federal Register / Vol. 78, No. 55 / Thursday, March 21, 2013 / Rules and Regulations
(ii) For Model 767–400ER series airplanes:
Boeing Service Bulletin 767–27–0205, dated
January 27, 2005; or Boeing Service Bulletin
767–27–0205, Revision 1, dated February 12,
2009.
(2) This paragraph provides credit for the
actions required by paragraphs (h) and (l) of
this AD, if the actions were performed before
the effective date of this AD using Boeing
Alert Service Bulletin 767–27A0224, dated
June 23, 2011, which is not incorporated by
reference.
(3) This paragraph provides credit for the
actions required by paragraph (i) of this AD,
if the actions were performed before the
effective date of this AD using Boeing Alert
Service Bulletin 767–49A0035, Revision 1,
dated December 11, 2003, which is not
incorporated by reference.
(4) This paragraph provides credit for the
actions required by paragraph (j) of this AD,
if the actions were performed before the
effective date of this AD using Boeing Alert
Service Bulletin 767–51A0027, dated
December 9, 2004 (for Model 767–200, –300,
and –300F series airplanes); or Boeing Alert
Service Bulletin 767–51A0028, dated
December 9, 2004 (for Model 767–400ER
series airplanes); which are not incorporated
by reference.
wreier-aviles on DSK5TPTVN1PROD with RULES
(n) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 9-ANMSeattle-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 (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.
(o) Related Information
For more information about this AD,
contact Kelly McGuckin, Aerospace
Engineer, Systems and Equipment Branch,
ANM–130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: (425) 917–
6490; fax: (425) 917–6590; email:
Kelly.McGuckin@faa.gov.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
VerDate Mar<14>2013
14:39 Mar 20, 2013
Jkt 229001
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) Boeing Service Bulletin 767–27–0204,
Revision 2, dated August 16, 2011.
(ii) Boeing Service Bulletin 767–27–0205,
Revision 2, dated August 30, 2011.
(iii) Boeing Service Bulletin 767–27A0224,
Revision 1, dated December 16, 2011.
(iv) Boeing Service Bulletin 767–49A0035,
Revision 2, dated June 2, 2006.
(v) Boeing Service Bulletin 767–51A0027,
Revision 1, dated October 12, 2006.
(vi) Boeing Service Bulletin 767–51A0028,
Revision 1, dated October 12, 2006.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington.
For information on the availability of this
material at the FAA, call 425–227–1221.
(5) 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
28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–05588 Filed 3–20–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0847; Directorate
Identifier 2008–NM–056–AD; Amendment
39–17375; AD 2013–05–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 777–200,
–200LR, –300, and –300ER series
airplanes. This AD was prompted by
fuel system reviews conducted by the
manufacturer. This AD requires doing
an inspection to identify the part
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
number of the motor-operated valve
(MOV) actuators of the main and center
fuel tanks; replacing certain MOV
actuators with new MOV actuators; and
measuring the electrical resistance of
the bond from the adapter plate to the
airplane structure, and doing corrective
actions if necessary. We are issuing this
AD to prevent electrical current from
flowing through an MOV actuator into
a fuel tank, which could create a
potential ignition source inside the fuel
tank. This condition, in combination
with flammable fuel vapors, could result
in a fuel tank explosion and consequent
loss of the airplane.
DATES: This AD is effective April 25,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of April 25, 2013.
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
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 https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document 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:
Rebel Nichols, Aerospace Engineer,
Propulsion Branch, ANM–140S, Seattle
Aircraft Certification Office (ACO),
FAA, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6509;
fax: 425–917–6590; email:
rebel.nichols@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to include an
E:\FR\FM\21MRR1.SGM
21MRR1
]]>Agencies
[Federal Register Volume 78, Number 55 (Thursday, March 21, 2013)]
[Rules and Regulations]
[Pages 17285-17290]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-05588]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 78, No. 55 / Thursday, March 21, 2013 / Rules
and Regulations
[[Page 17285]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22523; Directorate Identifier 2005-NM-058-AD;
Amendment 39-17379; AD 2013-05-07]
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 767 airplanes. This AD was prompted by reports
of stiff operation of the elevator pitch control system and jammed
elevator controls. This AD requires replacing pressure seal assemblies;
doing repetitive inspections for dirt, loose particles, or blockage of
the flanged tube and drain hole for the pressure seals, and corrective
action if necessary; replacing the aft air-intake duct assembly with a
new or modified assembly and installing a dripshield; and installing
gutters on the horizontal stabilizer center section and modifying the
side brace fittings. We are issuing this AD to prevent moisture from
collecting and freezing on the elevator control system components,
which could limit the ability of the flightcrew to make elevator
control inputs and result in reduced controllability of the airplane.
DATES: This AD is effective April 25, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of April 25,
2013.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 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, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document 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: Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: (425) 917-6490; fax: (425) 917-6590; email:
Kelly.McGuckin@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to include an airworthiness directive (AD) that
would apply to the specified products. That SNPRM published in the
Federal Register on August 9, 2012 (77 FR 47563). The original NPRM (70
FR 56386, September 27, 2005) proposed to require drilling a drain hole
in the flanged tubes for certain elevator control cable aft pressure
seals; doing repetitive inspections for dirt, loose particles, or
blockage of the flanged tube and drain hole for the pressure seals, and
corrective action if necessary; replacing the aft air-intake duct
assembly with a new or modified assembly and installing a dripshield;
and installing gutters on the horizontal stabilizer center section and
modifying the side brace fittings. The SNPRM proposed to revise the
NPRM by requiring replacement of pressure seal assemblies, rather than
the proposed drilling of drain holes; revising a certain compliance
time and inspection type; adding certain optional actions; and revising
the applicability.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the SNPRM (77
FR 47563, August 9, 2012) and the FAA's response to each comment. One
commenter, Natalia Budyldina, stated the SNPRM is significant since it
is related to airplane safety, would let the pilot better control the
airplane, and would reduce airplane delays due to technical problems.
Request To Allow Installing New or Modified Aft Air-Intake Duct
Assemblies
UPS requested that we revise paragraph (i) of the SNPRM (77 FR
47563, August 9, 2012) to clarify if operators are allowed to install a
``new or reworked duct'' on all affected airplanes or if operators must
strictly follow the service information. UPS stated that paragraph (i)
of the SNPRM requires installation of a ``new or modified'' aft air-
intake duct assembly in accordance with Boeing Service Bulletin 767-
49A0035, Revision 2, dated June 2, 2006, which specifies to install a
new duct assembly on the first airplane modified in an operator's fleet
and to install reworked duct assemblies on the operator's remaining
fleet.
We agree that installing either new or reworked duct assemblies on
all airplanes in an operator's fleet addresses the identified unsafe
condition. We have revised paragraph (i) of this AD to refer to new
paragraph (k)(8) of this AD, which states that where Boeing Service
Bulletin 767-49A0035, Revision 2, dated June 2, 2006, specifies
installing a new aft air-intake duct assembly on the first airplane in
each operator's fleet and installing a reworked aft air-intake duct
assembly on all remaining airplanes in each operator's fleet, this AD
requires installing either a new or reworked aft air-intake duct
assembly on all airplanes.
[[Page 17286]]
Request To Extend Compliance Time
Boeing requested that, for airplanes on which Boeing Service
Bulletin 767-27A0219 has been done, we extend the compliance time
specified in paragraph (g)(1)(ii) of the SNPRM (77 FR 47563, August 9,
2012) from 6 months to 24 months after the effective date of the AD for
the inspections specified in Boeing Service Bulletin 767-27-0204,
Revision 2, dated August 16, 2011; and Boeing Service Bulletin 767-27-
0205, Revision 2, dated August 30, 2011. Boeing stated that the 24-
month compliance time, which will allow operators to incorporate the
drain hole inspection into a standard maintenance interval, is
supported by the Boeing analysis in which the compliance recommendation
for Boeing Service Bulletin 767-27-0204, Revision 2, dated August 16,
2011; and Boeing Service Bulletin 767-27-0205, Revision 2, dated August
30, 2011, was formulated.
We agree. We have determined that, for airplanes on which Boeing
Service Bulletin 767-27A0219 has been done as of the effective date of
this AD, a compliance time of within 24 months will provide an
acceptable level of safety for accomplishing the inspection required by
paragraph (g) of this AD. We have revised paragraph (g)(1) of this AD
accordingly (and removed paragraphs (g)(1)(i) and (g)(1)(ii) of the
SNPRM (77 FR 47563, August 9, 2012)).
Request To Add Exception for Group 4 Airplanes Identified in Boeing
Service Bulletin 767-27A0224, Revision 1, Dated December 16, 2011
Boeing requested that we add an exception for Group 4 airplanes
identified in Boeing Service Bulletin 767-27A0224, Revision 1, dated
December 16, 2011, to allow operators that have replaced the
configuration having two seal plates (part numbers (P/Ns) 255T4847-1
and 65-28174-1) with the configuration having one seal plate (P/N
255T4847-5) to omit the removal/installation of the kept part, named
``SEAL PLATE ASSEMBLY,'' while performing Figures 7 through 10 of
Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16,
2011. Boeing also stated that Group 1 though 3 airplanes can use the
two-part configuration as an alternative to the one-part configuration
while performing Figure 1 and Figures 4 through 6 of Boeing Service
Bulletin 767-27A0224, Revision 1, dated December 16, 2011. Boeing
stated the installation of P/N 255T4847-5 is equivalent to the
combination of P/Ns 255T4847-1 and 65-28174-1 for the purposes of
Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16,
2011.
We agree to add an exception to this AD, for the reasons provided
by the commenter. We have revised paragraphs (h) and (l) of this AD to
refer to new paragraphs (k)(9) and (k)(10) of this AD:
Paragraph (k)(9) of this AD specifies, for Group 4
airplanes, as identified in Boeing Service Bulletin 767-27A0224,
Revision 1, dated December 16, 2011, that where Figures 7 through 10 of
Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16,
2011, specify to replace the seal plate assembly, this AD allows
replacing the configuration having two seal plates, P/Ns 255T4847-1 and
65-28174-1, with the configuration having one seal plate, P/N 255T4847-
5.
Paragraph (k)(10) to this AD specifies, for Group 1
through 3 airplanes, as identified in Boeing Service Bulletin 767-
27A0224, Revision 1, dated December 16, 2011, that where Figures 1 and
Figures 4 through 6 of Boeing Service Bulletin 767-27A0224, Revision 1,
dated December 16, 2011, specify to replace the seal plate, this AD
allows replacing the configuration having one seal plate, P/N 255T4847-
5, with the configuration having two seal plates, P/Ns 255T4847-1 and
65-28174-1.
Request for Exception To Allow Installation of Clamp
Boeing requested that we allow installation of a clamp, P/N AN735-(
), having a larger diameter than the clamp specified in steps 8 and 9
of Figure 4 and steps 8 and 9 of Figure 8 of Boeing Service Bulletin
767-27A0224, Revision 1, dated December 16, 2011. Boeing stated that
the existing flanged tube may have a repair that increases its diameter
and that installation of a clamp, P/N AN735-( ), of increased diameter
would be necessary in order to meet the clamp installation
specifications.
We agree to allow installation of the larger clamps, P/N AN735-( ),
as requested. We have revised paragraphs (h) and (l) to refer to new
paragraph (k)(11) of this AD, which specifies that where steps 8 and 9
of Figure 4 and steps 8 and 9 of Figure 8 of Boeing Service Bulletin
767-27A0224, Revision 1, dated December 16, 2011, specify installing
clamp P/N AN735-16, this AD allows, for airplanes having increased
diameter of the flanged tube due to a repair, installation of a clamp,
P/N AN735-( ), that has a larger diameter than P/N AN735-16.
Request To Allow Substitute Fasteners
Boeing requested that we allow substitute fasteners (bolts) for the
bolts specified in Figures 6 and 10 of Boeing Service Bulletin 767-
27A0224, Revision 1, dated December 16, 2011. Boeing stated that bolts,
P/N BACB30NT3K( ), BACB30LK3-( ), BACB30ZG3-( ), and NAS623-3-( ), are
substitutes for the bolts specified in steps 1 and 4 of Figure 6 and
steps 1 and 4 of Figure 10 of Boeing Service Bulletin 767-27A0224,
Revision 1, dated December 16, 2011. Boeing stated that airplanes were
delivered with those other equivalent part numbers and that the
structural repair manual may not specify that these bolts are
acceptable substitutes.
We agree to add an exception to this AD for the reason provided by
the commenter. We have revised paragraphs (h) and (l) to refer to new
paragraph (k)(12) of this AD, which specifies that where steps 1 and 4
of Figure 6 and steps 1 and 4 of Figure 10 of Boeing Service Bulletin
767-27A0224, Revision 1, dated December 16, 2011, specify installing
bolts, this AD allows installation of bolts having P/N BACB30NT3K( ),
BACB30LK3-( ), BACB30ZG3-( ), or NAS623-3-( ).
Request To Allow Exception for Operators That Have Done a Replacement
Boeing requested that we add an exception for airplanes identified
as Group 1, Configuration 2 through 4 airplanes, Group 2 and 3
airplanes, and Group 4, Configuration 2 through 4 airplanes, in Boeing
Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011 (we
referred to that service bulletin as the appropriate source of service
information for accomplishing the replacement required by paragraph (h)
of the SNPRM (77 FR 47563, August 9, 2012), and the optional
replacement specified in paragraph (l) of the SNPRM). Boeing stated the
exception would allow operators that replaced a flanged tube with a new
flanged tube as a repair (after accomplishing Boeing Service Bulletin
767-27A0224, Revision 1, dated December 16, 2011) to install the
replacement flanged tube without restoring the drain hole and clamp.
Boeing stated that replacement flanged tubes do not have a pre-drilled
drain hole, and it is unnecessary to restore the configuration with the
drain hole and clamp to cover the drain hole.
We disagree with the request to add an exception to this AD for
operators that have accomplished the replacement specified in paragraph
(h) or (l) of this AD. Boeing did not submit information (e.g., what
specific replacement parts are acceptable) to substantiate that this
method of compliance with paragraphs (h) and (l) of this AD addresses
the
[[Page 17287]]
identified unsafe condition. Once we issue this AD, any person may
request approval of an AMOC under the provisions of paragraph (n) of
this AD. We have not changed this AD in this regard.
Request To Confirm Credit for a Certain Boeing Service Bulletin
United Airlines requested we confirm that credit is provided for
previous accomplishment of Boeing Service Bulletin 767-51A0027,
Revision 1, dated October 12, 2006. United Airlines noted that
paragraph (m)(4) of the SNPRM (77 FR 47563, August 9, 2012) provides
credit for Boeing Alert Service Bulletin 767-51A0027, dated December 9,
2004.
We agree to clarify. This AD does provide credit for previous
accomplishment (i.e., before the effective date of this AD) of Boeing
Service Bulletin 767-51A0027, Revision 1, dated October 12, 2006 (the
appropriate source of service information for certain Model 767-200, -
300, and -300F series airplanes for accomplishing the actions required
by paragraph (j) of this AD). Paragraph (f) of this AD states: ``Comply
with this AD within the compliance times specified, unless already
done.'' The intent of paragraph (f) of this AD is to allow credit for
previous accomplishment of the service information required by the AD.
For previous issues of required service information, each AD
specifies in a separate paragraph whether credit is given for those
previous issues. Paragraph (m)(4) of this AD provides credit for Boeing
Alert Service Bulletin 767-51A0027, dated December 9, 2004, which is
the previous issue of the required service bulletin, Boeing Service
Bulletin 767-51A0027, Revision 1, dated October 12, 2006. We have not
changed this AD in this regard.
Request To Clarify Paragraphs (g) and (h) of the SNPRM (77 FR 47563,
August 9, 2012)
UPS requested that we clarify the requirements of paragraphs (g)
and (h) of the SNPRM (77 FR 47563, August 9, 2012). UPS stated that
paragraph (g) of the SNPRM requires inspections in accordance with the
work instructions contained in Boeing Service Bulletin 767-27-0204,
Revision 2, dated August 16, 2011, and that Boeing Service Bulletin
767-27-0204, Revision 2, dated August 16, 2011, lists Boeing Service
Bulletin 767-27A0219, Revision 1, dated February 12, 2009, as a
``concurrent requirement.'' UPS asked if the intent of paragraph (g) of
the SNPRM is to mandate the inspections without the ``concurrent
requirement'' of the modification specified in Boeing Service Bulletin
767-27A0219, Revision 1, dated February 12, 2009. UPS stated that if
the intent is to require the inspections and the modifications, then
paragraph (h) of the SNPRM should read: ``Accomplishing this
replacement terminates the inspections and modification required by
paragraph (g) of this AD.''
We agree to clarify. Paragraph (g) of this AD requires that
inspections specified in Boeing Service Bulletin 767-27-0204, Revision
2, dated August 16, 2011, be done. The compliance time for doing those
inspections is dependent on whether or not any revision of ``Boeing
Service Bulletin 767-27A0219'' has been done, as specified in
paragraphs (g)(1) and (g)(2) of this AD; however, paragraph (g) of this
AD does not require that the modification specified in Boeing Service
Bulletin 767-27A0219, Revision 1, dated February 12, 2009, must be
done. We have not changed this AD in this regard.
Request for Flexibility in Use of Abrasive
UPS requested that we allow flexibility in the use of abrasive
specified in Figure 5 of Boeing Service Bulletin 767-27A0224, Revision
1, dated December 16, 2011. UPS stated that paragraph (h) of the SNPRM
(77 FR 47563, August 9, 2012) would require accomplishment of that
service bulletin. (Paragraph (l) of the SNPRM would also require that
service bulletin, if the actions in paragraph (l) of the SNPRM are
done.) UPS stated that Figure 5 specifies to use an abrasive to prepare
for adhesive application and that ``80-grit is recommended.'' UPS also
noted that Figure 5 refers to standard overhaul practices manual (SOPM)
20-50-12 for adhesive mixing and surface cleaning. UPS asked if
operators are allowed the flexibility offered by the SOPM.
We agree that there is flexibility in the use of abrasive specified
in Figure 5 of Boeing Service Bulletin 767-27A0224, Revision 1, dated
December 16, 2011. There is no requirement in this AD that mandates the
use of 80-grit abrasive. As noted by the commenter, Figure 5 of Boeing
Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011, only
recommends the use of 80-grit abrasive and includes a reference to SOPM
20-50-12. Similarly, Figures 4, 8, and 9 of Boeing Service Bulletin
767-27A0224, Revision 1, dated December 16, 2011, only recommend the
use of 80-grit abrasive. Operators may use an abrasive of the specific
grit referenced in SOPM 20-50-12 to accomplish the actions specified in
steps 1 and 2 of Figures 4, 5, 8, and 9 of Boeing Service Bulletin 767-
27A0224, Revision 1, dated December 16, 2011. We have not changed this
AD in this regard.
Request To Revise Effectivity Listed in the Preamble of the SNPRM (77
FR 47563, August 9, 2012)
Boeing requested that we revise the effectivity for Boeing Service
Bulletin 767-27-0204, Revision 2, dated August 16, 2011, specified in
the ``Actions Since Previous NPRM (70 FR 56386, September 27, 2005) was
Issued'' section of the preamble of the SNPRM (77 FR 47563, August 9,
2012). Boeing stated that the effectivity listed in the SNPRM should be
revised to include line numbers 972 through 974 to match the
effectivity listed in Boeing Service Bulletin 767-27-0204, Revision 2,
dated August 16, 2011.
We acknowledge that the effectivity of Boeing Service Bulletin 767-
27-0204, Revision 2, dated August 16, 2011, is line numbers 225, 226,
228 through 717, and 719 through 971, except airborne warning and
control system (AWACS) airplanes; and line numbers 972 through 974.
However, the ``Actions Since Previous NPRM (70 FR 56386, September 27,
2005) was Issued'' section of the SNPRM (77 FR 47563, August 9, 2012)
is not restated in this AD. We have not changed this AD in this regard.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously--and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM (77 FR 47563, August 9, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM (77 FR 47563, August 9, 2012).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects about 400 airplanes of U.S.
registry.
We estimate the following costs to comply with this AD:
[[Page 17288]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection of the flanged tube 2 work-hours x $85 $0 $170 per inspection $51,000 per
and drain hole (300 airplanes). per hour = $170 cycle. inspection cycle.
per inspection
cycle.
Pressure seal replacement (300 7 work-hours x $85 261 $856............... $256,800.
airplanes). per hour = $595.
Aft air-intake duct assembly 3 work-hours x $85 1,462 $1,717............. $614,686.
replacement and dripshield per hour = $255.
installation (358 airplanes).
Horizontal stabilizer gutter 12 work-hours x $85 1,902 $2,922............. $1,034,388.
installation and modification of per hour = $1,020.
the side brace fittings (354
airplanes).
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary cleaning that
would be required based on the results of the inspection. We have no
way of determining the number of aircraft that might need this
cleaning.
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Cleaning...................................... 1 work-hour x $85 per hour = $85 $0 $85
----------------------------------------------------------------------------------------------------------------
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):
2013-05-07 The Boeing Company: Amendment 39-17379; Docket No. FAA-
2005-22523; Directorate Identifier 2005-NM-058-AD.
(a) Effective Date
This AD is effective April 25, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes, certificated in any category; as
identified in the service information specified in paragraphs
(c)(1), (c)(2), (c)(3), (c)(4), (c)(5), and (c)(6) of this AD.
(1) Boeing Service Bulletin 767-27A0224, Revision 1, dated
December 16, 2011.
(2) Boeing Service Bulletin 767-49A0035, Revision 2, dated June
2, 2006.
(3) Boeing Service Bulletin 767-27-0204, Revision 2, dated
August 16, 2011.
(4) Boeing Service Bulletin 767-27-0205, Revision 2, dated
August 30, 2011.
(5) Boeing Service Bulletins 767-51A0027, Revision 1, dated
October 12, 2006.
(6) Boeing Service Bulletin 767-51A0028, Revision 1, dated
October 12, 2006.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 27, Flight controls; 49, Airborne auxiliary
power; and 51, Standard practices/structures.
(e) Unsafe Condition
This AD was prompted by reports of stiff operation of the
elevator pitch control system and jammed elevator controls. We are
issuing this AD to prevent moisture from collecting and freezing on
the elevator control system components, which could limit the
ability of the flightcrew to make elevator control inputs and result
in reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 17289]]
(g) Inspections and Corrective Actions
For airplanes identified in Boeing Service Bulletin 767-27-0204,
Revision 2, dated August 16, 2011; and Boeing Service Bulletin 767-
27-0205, Revision 2, dated August 30, 2011: At the applicable time
specified in paragraph (g)(1) or (g)(2) of this AD, do a general
visual inspection for dirt, loose particles, and blockage of the
flanged tube and drain hole for the E1A and E1B elevator control
cable aft pressure seals, and all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 767-27-0204, Revision 2, dated August 16, 2011 (for Model
767-200, -300, and -300F series airplanes); or Boeing Service
Bulletin 767-27-0205, Revision 2, dated August 30, 2011 (for Model
767-400ER series airplanes). Do all applicable corrective actions
before further flight. Repeat the inspection thereafter at intervals
not to exceed 24 months.
(1) For airplanes on which Boeing Service Bulletin 767-27A0219
has been done as of the effective date of this AD: Within 24 months
after the effective date of this AD.
(2) For airplanes on which Boeing Service Bulletin 767-27A0219
has not been done as of the effective date of this AD: Do the
inspection at the time specified in paragraph (g)(2)(i) or
(g)(2)(ii) of this AD, whichever occurs later.
(i) Within 24 months after the effective date of this AD.
(ii) Within 24 months since the date of issuance of the original
airworthiness certificate or the date of issuance of the original
export certificate of airworthiness.
(h) Replacement--Pressure Seal Assemblies
For Group 1, Configuration 1 and 2 airplanes; Group 2,
Configuration 1 airplanes; and Group 4, Configuration 1 and 2
airplanes; as identified in Boeing Service Bulletin 767-27A0224,
Revision 1, dated December 16, 2011: Within 24 months after the
effective date of this AD, replace the two existing pressure seal
assemblies for the left elevator control cables at the aft pressure
bulkhead, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 767-27A0224, Revision 1, dated December 16,
2011, except as provided by paragraphs (k)(9), (k)(10), (k)(11), and
(k)(12) of this AD. Accomplishing this replacement terminates the
inspections required by paragraph (g) of this AD.
(i) Replacement--Air-Intake Duct Assembly and Installation--Dripshield
For airplanes identified in Boeing Service Bulletin 767-49A0035,
Revision 2, dated June 2, 2006: Within 18 months after the effective
date of this AD, replace the aft air-intake duct assembly with a new
or modified aft air-intake duct assembly and install a dripshield,
in accordance with the Accomplishment Instructions of Boeing Service
Bulletin 767-49A0035, Revision 2, dated June 2, 2006, except as
provided by paragraphs (k)(1) and (k)(8) of this AD.
(j) Gutter Installation and Side Brace Modification
For airplanes identified in Boeing Service Bulletin 767-51A0027,
Revision 1, dated October 12, 2006; and Boeing Service Bulletin 767-
51A0028, Revision 1, dated October 12, 2006: Within 60 months after
the effective date of this AD, install gutters on the horizontal
stabilizer center section, and modify the side brace fittings,
including doing a dye penetrant or high frequency eddy current
inspection for cracking and damage of the drain hole and all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 767-51A0027, Revision 1,
dated October 12, 2006 (for Model 767-200, -300, and -300F series
airplanes); or Boeing Service Bulletin 767-51A0028, Revision 1,
dated October 12, 2006 (for Model 767-400ER series airplanes);
except as provided by paragraphs (k)(2), (k)(3), (k)(4), (k)(5),
(k)(6), and (k)(7) of this AD.
(k) Exceptions to Service Information
(1) Where step 1 of Figure 4 of Boeing Service Bulletin 767-
49A0035, Revision 2, dated June 2, 2006, specifies installing the
forward air-intake duct, that installation is not required by this
AD.
(2) Where Boeing Service Bulletin 767-51A0027, Revision 1, dated
October 12, 2006; and Boeing Service Bulletin 767-51A0028, Revision
1, dated October 12, 2006; specify to contact Boeing for appropriate
action: Before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (n) of this
AD.
(3) Where step 8 in Figures 6 and 10 of Boeing Service Bulletin
767-51A0027, Revision 1, dated October 12, 2006; and Boeing Service
Bulletin 767-51A0028, Revision 1, dated October 12, 2006; specify
hydraulic hose, part number (P/N) AS115-08D0274, the correct part
number is AS115-08D0280.
(4) For steps 4, 8, and 12 in Figures 6 and 10 of Boeing Service
Bulletin 767-51A0027, Revision 1, dated October 12, 2006; and Boeing
Service Bulletin 767-51A0028, Revision 1, dated October 12, 2006:
Hydraulic hose, P/N AS115-08K0280, is an option to P/N AS115-
08D0280.
(5) For steps 2, 6, and 10 in Figures 6 and 10 of Boeing Service
Bulletin 767-51A0027, Revision 1, dated October 12, 2006; and Boeing
Service Bulletin 767-51A0028, Revision 1, dated October 12, 2006:
Hydraulic hose, P/N AS115-06K0274, is an option to P/N AS115-
06D0274.
(6) Steps 3.B.16 and 3.B.17 of Boeing Service Bulletin 767-
51A0027, Revision 1, dated October 12, 2006; and Boeing Service
Bulletin 767-51A0028, Revision 1, dated October 12, 2006; are not
required by this AD.
(7) Where note (d) of Figure 8 of Boeing Service Bulletin 767-
51A0027, Revision 1, dated October 12, 2006; and Boeing Service
Bulletin 767-51A0028, Revision 1, dated October 12, 2006; specifies
to ``install collars on the upper surface of the gutter,'' this AD
requires that operators install these bolts with the bolt heads
either up or down provided that the bolt head direction prevents
interference between the collars and the hydraulic lines.
(8) Where Boeing Service Bulletin 767-49A0035, Revision 2, dated
June 2, 2006, specifies installing a new aft air-intake duct
assembly on the first airplane in each operator's fleet and
installing a reworked aft air-intake duct assembly on all remaining
airplanes in each operator's fleet, this AD requires installing
either a new or reworked aft air-intake duct assembly on all
airplanes.
(9) For Group 4 airplanes, as identified in Boeing Service
Bulletin 767-27A0224, Revision 1, dated December 16, 2011: Where
Figures 7 through 10 of Boeing Service Bulletin 767-27A0224,
Revision 1, dated December 16, 2011, specify to replace the seal
plate assembly, this AD allows replacing the configuration having
two seal plates, P/Ns 255T4847-1 and 65-28174-1, with the
configuration having one seal plate, P/N 255T4847-5.
(10) For Group 1 through 3 airplanes, as identified in Boeing
Service Bulletin 767-27A0224, Revision 1, dated December 16, 2011:
Where Figures 1 and Figures 4 through 6 of Boeing Service Bulletin
767-27A0224, Revision 1, dated December 16, 2011, specify to replace
the seal plate, this AD allows replacing the configuration having
one seal plate, P/N 255T4847-5 with the configuration having two
seal plates, P/Ns 255T4847-1 and 65-28174-1.
(11) Where steps 8 and 9 of Figure 4 and steps 8 and 9 of Figure
8 of Boeing Service Bulletin 767-27A0224, Revision 1, dated December
16, 2011, specify installing clamp P/N AN735-16, this AD allows, for
airplanes having increased diameter of the flanged tube due to a
repair, installation of a clamp, P/N AN735-( ), that has a larger
diameter than P/N AN735-16.
(12) Where steps 1 and 4 of Figure 6 and steps 1 and 4 of Figure
10 of Boeing Service Bulletin 767-27A0224, Revision 1, dated
December 16, 2011, specify installing bolts, this AD allows
installation of bolts having P/N BACB30NT3K( ), BACB30LK3-( ),
BACB30ZG3-( ), or NAS623-3-( ).
(l) Optional Replacement--Pressure Seal Assemblies
For Group 1, Configuration 3 and 4 airplanes; Group 2,
Configuration 2 and 3 airplanes; Group 3 airplanes; and Group 4,
Configuration 3 and 4 airplanes; as identified in Boeing Service
Bulletin 767-27A0224, Revision 1, dated December 16, 2011: Replacing
the two existing pressure seal assemblies for the left elevator
control cables at the aft pressure bulkhead, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 767-27A0224,
Revision 1, dated December 16, 2011, except as provided by
paragraphs (k)(9), (k)(10), (k)(11), and (k)(12) of this AD,
terminates the inspections required by paragraph (g) of this AD.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if the actions were performed before the
effective date of this AD using the applicable service information
in paragraph (m)(1)(i) or (m)(1)(ii) of this AD, which are not
incorporated by reference.
(i) For Model 767-200, -300, and -300F series airplanes: Boeing
Service Bulletin 767-27-0204, dated January 27, 2005; or Boeing
Service Bulletin 767-27-0204, Revision 1, dated February 12, 2009.
[[Page 17290]]
(ii) For Model 767-400ER series airplanes: Boeing Service
Bulletin 767-27-0205, dated January 27, 2005; or Boeing Service
Bulletin 767-27-0205, Revision 1, dated February 12, 2009.
(2) This paragraph provides credit for the actions required by
paragraphs (h) and (l) of this AD, if the actions were performed
before the effective date of this AD using Boeing Alert Service
Bulletin 767-27A0224, dated June 23, 2011, which is not incorporated
by reference.
(3) This paragraph provides credit for the actions required by
paragraph (i) of this AD, if the actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin 767-
49A0035, Revision 1, dated December 11, 2003, which is not
incorporated by reference.
(4) This paragraph provides credit for the actions required by
paragraph (j) of this AD, if the actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin 767-
51A0027, dated December 9, 2004 (for Model 767-200, -300, and -300F
series airplanes); or Boeing Alert Service Bulletin 767-51A0028,
dated December 9, 2004 (for Model 767-400ER series airplanes); which
are not incorporated by reference.
(n) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(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
(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.
(o) Related Information
For more information about this AD, contact Kelly McGuckin,
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA,
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton,
WA 98057-3356; phone: (425) 917-6490; fax: (425) 917-6590; email:
Kelly.McGuckin@faa.gov.
(p) 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) Boeing Service Bulletin 767-27-0204, Revision 2, dated
August 16, 2011.
(ii) Boeing Service Bulletin 767-27-0205, Revision 2, dated
August 30, 2011.
(iii) Boeing Service Bulletin 767-27A0224, Revision 1, dated
December 16, 2011.
(iv) Boeing Service Bulletin 767-49A0035, Revision 2, dated June
2, 2006.
(v) Boeing Service Bulletin 767-51A0027, Revision 1, dated
October 12, 2006.
(vi) Boeing Service Bulletin 767-51A0028, Revision 1, dated
October 12, 2006.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) 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 28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-05588 Filed 3-20-13; 8:45 am]
BILLING CODE 4910-13-P
