[Federal Register Volume 78, Number 55 (Thursday, March 21, 2013)]
[Rules and Regulations]
[Pages 17285-17290]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-05588]
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Rules and Regulations
Federal Register
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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 http://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:
[email protected].
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: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes 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:
[email protected].
(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: http://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