[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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  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