[Federal Register Volume 78, Number 38 (Tuesday, February 26, 2013)]
[Proposed Rules]
[Pages 12991-12995]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-04338]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0095; Directorate Identifier 2011-NM-197-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede two existing airworthiness directives 
(AD) that apply to all The Boeing Company Model 767 airplanes. One AD 
currently requires a functional check of the shear rivets in all six 
elevator power control actuator (PCA) bellcrank assemblies to determine 
the condition of the shear rivets, and replacement or rework of the 
bellcrank assemblies if necessary. The other AD currently requires 
repetitive testing of the elevator control system to determine if an 
elevator PCA is rigged incorrectly, and follow-on actions if necessary. 
Since we issued those ADs, a terminating modification has been 
designed. This proposed AD would require an inspection to determine the 
part numbers and condition of the bellcrank assemblies; modification or 
replacement of the PCA bellcrank assembly, if necessary; and a 
repetitive functional test and mis-rig check, and corrective actions if 
necessary. We are proposing this AD to prevent continued operation with 
yielded or failed shear rivets in the elevator PCA bellcrank 
assemblies, and to prevent certain failures or jams in the elevator 
system from causing a hardover of the elevator surface, resulting in a 
significant pitch upset and possible loss of control of the airplane.

DATES: We must receive comments on this proposed AD by April 12, 2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 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 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Marie Hogestad, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6418; fax: 425-917-6590; email: marie.hogestad@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0095; 
Directorate Identifier 2011-NM-197-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On August 18, 2000, we issued AD 2000-17-05, Amendment 39-11879 (65 
FR 51754, August 25, 2000), for certain The Boeing Company Model 767-
200, -300, and -300F series airplanes. That AD requires a one-time 
functional check of the shear rivets in all six PCA bellcrank 
assemblies to determine the condition of the shear rivets; and 
replacement or rework of the bellcrank assemblies, if necessary. That 
AD resulted from reports that elevator bellcrank assemblies with failed 
shear rivets had been found on three Model 767 airplanes. We issued 
that AD to detect and correct any failed or partially yielded shear 
rivets of the elevator PCA bellcrank assemblies. Failure of two 
bellcrank assemblies on one side can result in that single elevator 
surface moving to a hardover position, independent of pilot command, 
resulting in a significant pitch upset recoverable by the crew. Failure 
of three bellcrank assemblies on one side could result in loss of 
control of the airplane.
    On February 21, 2001, we issued AD 2001-04-09, Amendment 39-12128 
(66 FR 13227, March 5, 2001), for all The Boeing Company Model 767 
airplanes. That AD requires repetitive testing of the elevator control 
system to determine if an elevator PCA is rigged incorrectly due to 
yielded or failed shear rivets in a bellcrank assembly of the elevator 
PCA, and follow-on actions if necessary. That AD resulted from reports 
that several Model 767 airplanes failed the one-time functional check 
of the shear rivets in the bellcrank assemblies of the elevator PCA 
required by AD 2000-17-05, Amendment 39-11879 (65 FR 51754, August 25, 
2000). We issued AD 2001-04-09, Amendment 39-12128 (66 FR 13227, March 
5, 2001), to prevent continued operation with yielded or failed shear 
rivets in a bellcrank assembly of the elevator PCA, which could result 
in loss of control of the airplane.

Actions Since Existing AD 2000-17-05, Amendment 39-11879 (65 FR 51754, 
August 25, 2000); and AD 2001-04-09, Amendment 39-12128 (66 FR 13227, 
March 5, 2001) Issued

    The preambles to AD 2000-17-05, Amendment 39-11879 (65 FR 51754, 
August 25, 2000); and AD 2001-04-09, Amendment 39-12128 (66 FR 13227,

[[Page 12992]]

March 5, 2001); specify that we consider the requirements ``interim 
action.'' Those ADs explain that we might consider further rulemaking 
if a modification is developed, approved, and available. The 
manufacturer now has developed such a modification, and we have 
determined that further rulemaking is indeed necessary; this proposed 
AD follows from that determination.

Relevant Service Information

    We reviewed Boeing Service Bulletins 767-27-0186, dated June 25, 
2007 (for Model 767-200, -300, and -300F series airplanes); and 767-27-
0187, dated June 25, 2007 (for Model 767-400ER series airplanes). This 
service information describes procedures for doing a general visual 
inspection of the PCA bellcrank assemblies on each elevator to 
determine if the bellcrank assembly has shear rivets; and installing a 
solid elevator PCA bellcrank assembly or reworking the bellcrank 
assembly to replace the shear rivets with solid rivets, if necessary. 
This service information also describes procedures for the initial test 
of the elevator PCA input rod assemblies (pogo check), and replacement 
or overhaul if necessary; and an elevator PCA rigging check.
    We also reviewed Boeing Service Bulletins 767-27-0200, dated June 
25, 2007 (for Model 767-200, -300, and -300F series airplanes); and 
767-27-0201, dated June 27, 2007 (for Model 767-400ER series 
airplanes). This service information describes procedures for 
repetitive testing of the elevator PCA input rod assemblies (pogo 
check), and replacing or overhauling the elevator PCA input rod 
assembly, if necessary.
    We reviewed Boeing Service Bulletins 767-27-0202, Revision 1, dated 
February 21, 2008 (for Model 767-200, -300, and -300F series 
airplanes); and 767-27-0203, Revision 1, dated February 21, 2008 (for 
Model 767-400ER series airplanes). This service information describes 
procedures for doing repetitive checks of the elevator PCA rigging, and 
adjusting the PCA input rod assemblies and structural inspection, if 
necessary.

Other Relevant Rulemaking

    AD 2007-24-08, Amendment 39-15274 (72 FR 67236, November 28, 2007), 
was issued for Model 767 airplanes. That AD requires repetitive 
measurements of the rudder and elevator freeplay, related investigative 
and corrective actions if necessary, and repetitive lubrications of the 
rudder and elevator components. For certain airplanes, we require 
concurrent actions.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain certain requirements of AD 2000-17-
05, Amendment 39-11879 (65 FR 51754, August 25, 2000); and AD 2001-04-
09, Amendment 39-12128 (66 FR 13227, March 5, 2001). This proposed AD 
would require an inspection to determine the part numbers and condition 
of the bellcrank assemblies; modification or replacement of the PCA 
bellcrank assembly, if necessary; and repetitive post-modification 
testing and corrective actions, if necessary. This proposed AD would 
also require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between the Proposed AD and the Service Information.''

Change to Existing AD 2001-04-09 (66 FR 13227, March 5, 2001) and AD 
2000-17-05, Amendment 39-11879 (65 FR 51754, August 25, 2000)

    Boeing Commercial Airplanes has received an Organization 
Designation Authorization (ODA). We have revised this proposed AD to 
delegate the authority to approve an alternative method of compliance 
for any repair required by this proposed AD to the Boeing Commercial 
Airplanes ODA rather than a Designated Engineering Representative 
(DER).
    Since AD 2000-17-05, Amendment 39-11879 (65 FR 51754, August 25, 
2000); and AD 2001-04-09, Amendment 39-12128 (66 FR 13227, March 5, 
2001); were issued, the AD format has been revised, and certain 
paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                          Corresponding  requirement in
      Requirement in previous AD                this proposed AD
------------------------------------------------------------------------
Paragraph (a) of AD 2000-17-05,         paragraph (g).
 Amendment 39-11879 (65 FR 51754,
 August 25, 2000).
Paragraph (b) of AD 2000-17-05........  paragraph (g)(4).
Paragraph (a) of AD 2001-04-09,         paragraph (h).
 Amendment 39-12128 (66 FR 13227,
 March 5, 2001).
Paragraph (b) of AD 2001-04-09........  paragraph (i).
------------------------------------------------------------------------

    In addition, we have revised certain headings pertaining to 
restated material throughout this AD.

Differences Between the Proposed AD and the Service Information

    This proposed AD will allow for an alternate grease (BMS 3-33) when 
accomplishing the actions specified in Boeing Service Bulletins 767-27-
0186 and 767-27-0187, both dated June 25, 2007.
    Although Boeing Service Bulletins 767-27-0202 and 767-27-0203, both 
Revision 1, both dated February 21, 2008, do not specify a corrective 
action following a structural inspection, this proposed AD would 
require operators to repair conditions using a method approved by the 
FAA.

Costs of Compliance

    We estimate that this proposed AD affects 415 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 12993]]



                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                 U.S.
              Action                        Labor cost           Parts cost   airplanes     Cost per  product             Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Functional check of the shear       4 work-hours x $85 per               $0          330  $340.................  $112,200.
 rivets (existing requirement for    hour = $340.
 AD 2000-17-05, Amendment 39-11879
 (65 FR 51754, August 25, 2000)).
Repetitive inspection of bellcrank  2 work-hours x $85 per                0          335  $170 per inspection    $56,950 per inspection cycle.
 assemblies (existing requirement    hour = $170 per                                       cycle.
 for AD 2001-04-09, Amendment 39-    inspection cycle.
 12128 (66 FR 13227, March 5,
 2001)).
Inspection of elevator PCA          23 work-hours x $85 per               0          390  $1,955...............  $762,450.
 bellcrank assemblies, functional    hour = $1,955.
 test (pogo check), and elevator
 mis-rig check (new proposed
 actions for Model 767 airplanes
 having line numbers 1-901).
Repetitive functional test (pogo    32 work-hours x $85 per               0          415  $2,720 per inspection  $1,128,800 per inspection cycle.
 check) (new proposed action for     hour = $2,720 per                                     cycle.
 all Model 767 airplanes).           inspection cycle.
Repetitive elevator mis-rig check   2 work-hours x $85 per                0          415  $170 per inspection    $70,550 per inspection cycle.
 (new proposed action for all        hour = $170 per                                       cycle.
 Model 767 airplanes).               inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs or 
replacements that would be required based on the results of the 
proposed inspection, tests, and checks. We have no way of determining 
the number of aircraft that might need these repairs or replacements.
    We estimate that reworking the bellcrank assembly would take about 
6 work-hours, for a labor cost of $510 per airplane; however, we have 
no definitive data to determine the cost of parts required. We have 
received no definitive data that would enable us to provide a cost 
estimate for replacing or overhauling the elevator PCA input rod 
assembly, adjusting the elevator PCA input rod assemblies, and doing 
structural inspections specified in this proposed AD.
    According to the manufacturer, some of the costs of this proposed 
AD might be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directives 
(ADs) 2000-17-05, Amendment 39-11879 (65 FR 51754, August 25, 2000); 
and 2001-04-09, Amendment 39-12128 (66 FR 13227, March 5, 2001); and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2013-0095; Directorate Identifier 
2011-NM-197-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by April 12, 
2013.

(b) Affected ADs

    This AD supersedes AD 2000-17-05, Amendment 39-11879 (65 FR 
51754, August 25, 2000); and AD 2001-04-09, Amendment 39-12128 (66 
FR 13227, March 5, 2001). This AD affects AD 2007-24-08, Amendment 
39-15274 (72 FR 67236, November 28, 2007).

[[Page 12994]]

(c) Applicability

    This AD applies to all The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 27, Flight controls.

(e) Unsafe Condition

    This AD was prompted by reports of failed shear rivets in the 
bellcrank assemblies of the elevator power control actuator (PCA). 
We are issuing this AD to prevent continued operation with yielded 
or failed shear rivets in the elevator PCA bellcrank assemblies, and 
to prevent certain failures or jams in the elevator system from 
causing a hardover of the elevator surface, resulting in a 
significant pitch upset and possible loss of control of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Functional Check

    This paragraph restates the requirements of paragraph (a) of AD 
2000-17-05, Amendment 39-11879 (65 FR 51754, August 25, 2000). For 
Model 767-200, -300, and -300F series airplanes, line numbers 1 
through 800 inclusive: Within 30 days after September 11, 2000 (the 
effective date AD 2000-17-05), perform a functional check of one 
shear rivet in all six elevator PCA bellcrank assemblies to 
determine the condition of the shear rivets, in accordance with 
Paragraph 3 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 767-27A0166, dated August 17, 2000. Doing the 
actions required by paragraphs (j), (k), and (l) of this AD 
terminates the requirements of paragraph (g) of this AD.
    (1) If all penetration depths, when measured per Figure 2 of 
Boeing Alert Service Bulletin 767-27A0166, dated August 17, 2000, 
are 0.50 inch or more, no further action is required by paragraph 
(g) of this AD.
    (2) If any penetration depth, when measured per Figure 2 of 
Boeing Alert Service Bulletin 767-27A0166, dated August 17, 2000, is 
0.35 inch or more, but less than 0.50 inch, rework or replace the 
bellcrank assembly with a new or serviceable bellcrank assembly 
within 400 flight hours after accomplishing the functional check. 
After installation of a new or serviceable bellcrank assembly, and 
prior to further flight, repeat the functional check of all the 
bellcrank assemblies to make sure the rivets are still in good 
condition (as specified in Boeing Alert Service Bulletin 767-
27A0166, dated August 17, 2000) after installation, in accordance 
with Figure 2 of Boeing Alert Service Bulletin 767-27A0166, dated 
August 17, 2000.
    (3) If any penetration depth, when measured per Figure 2 of 
Boeing Alert Service Bulletin 767-27A0166, dated August 17, 2000, is 
less than 0.35 inch, prior to further flight, rework or replace the 
bellcrank assembly with a new or serviceable bellcrank assembly. 
After installation of a new or serviceable bellcrank assembly, and 
prior to further flight, repeat the functional check of all the 
bellcrank assemblies to make sure the rivets are still in good 
condition (as specified in Boeing Alert Service Bulletin 767-
27A0166, dated August 17, 2000) after installation, in accordance 
with Figure 2 of Boeing Alert Service Bulletin 767-27A0166, dated 
August 17, 2000.

(h) Retained Repetitive Tests

    This paragraph restates the requirements of paragraph (a) of AD 
2001-04-09, Amendment 39-12128 (66 FR 13227, March 5, 2001), with 
revised provisions for repetitive tests. For all airplanes: Within 
90 days after March 20, 2001 (the effective date of AD 2001-04-09), 
perform a test of the elevator PCA bellcranks to determine if an 
elevator PCA is rigged incorrectly due to yielded or failed shear 
rivets in a bellcrank assembly, in accordance with Boeing Alert 
Service Bulletin 767-27A0168 (for Model 767-200, -300, and -300F 
series airplanes) or 767-27A0169 (for Model 767-400ER series 
airplanes), both dated November 21, 2000. Repeat the test thereafter 
at least every 400 flight hours. As of March 20, 2001 (the effective 
date of AD 2001-04-09), and until the accomplishment of the actions 
required by paragraphs (j), (k), and (l) of this AD, as applicable. 
Accomplishment of the repetitive tests required by paragraph (h) of 
this AD are acceptable for compliance with the functional check of 
the elevator system required by a certification maintenance 
requirement (CMR) that is documented as Item Number 27-31-00-5B in 
the Boeing 767 Maintenance Planning Document (MPD). Doing the 
actions required by paragraphs (j), (k), and (l) of this AD 
terminates the requirements of paragraph (h) of this AD. After 
accomplishment of the actions required by paragraphs (j), (k), and 
(l) of this AD, accomplishment of the repetitive tests required by 
paragraph (h) of this AD are not acceptable for compliance with the 
functional check of the elevator system required by a CMR that is 
documented as Item Number 27-31-00-5B in the Boeing 767 MPD.

(i) Retained Follow-On Actions

    This paragraph restates the requirements of paragraph (b) of AD 
2001-04-09, Amendment 39-12128 (66 FR 13227, March 5, 2001). For all 
airplanes: If an elevator PCA is determined to be rigged incorrectly 
during any test required by paragraph (h) of this AD, before further 
flight, do a one-time inspection to measure penetration depth of the 
shear rivets of all three elevator bellcrank assemblies of the 
affected elevator surface, in accordance with Boeing Alert Service 
Bulletin 767-27A0168 (for Model 767-200, -300, and -300F series 
airplanes) or 767-27A0169 (for Model 767-400ER series airplanes), 
both dated November 21, 2000. Doing the actions required by 
paragraphs (j), (k), and (l) of this AD terminates the requirements 
of paragraph (i) of this AD.
    (1) If the measured penetration depth of the shear rivets on all 
bellcrank assemblies is 0.50 inch or more: Before further flight, 
re-rig the elevator PCA correctly, in accordance with Boeing Alert 
Service Bulletin 767-27A0168 (for Model 767-200, -300, and -300F 
series airplanes) or 767-27A0169 (for Model 767-400ER series 
airplanes), both dated November 21, 2000.
    (2) If the measured shear rivet penetration depth on any single 
bellcrank assembly is less than 0.50 inch: Before further flight, 
repair the bellcrank assembly by replacing the shear rivets or 
replace the bellcrank assembly, and reassemble and re-rig the 
elevator control system, in accordance with Boeing Alert Service 
Bulletin 767-27A0168 (for Model 767-200, -300, and -300F series 
airplanes) or 767-27A0169 (for Model 767-400ER series airplanes), 
both dated November 21, 2000.

(j) New Inspection and Modification

    For airplanes having line numbers 1 through 901 inclusive: 
Within 72 months after the effective date of this AD, do a general 
visual inspection of the three PCA bellcrank assemblies on each 
elevator to determine the part numbers (P/Ns) of the bellcrank 
assemblies and to determine whether the bellcrank assembly has shear 
rivets, in accordance with the Accomplishment Instructions of Boeing 
Service Bulletin 767-27-0186, dated June 25, 2007 (for Model 767-
200, -300, and -300F series airplanes); or 767-27-0187, dated June 
25, 2007 (for Model 767-400ER series airplanes).
    (1) If the bellcrank assembly has P/N 252T2118-4 or 252T2118-5, 
and has solid rivets, no further action is required by this 
paragraph.
    (2) If the bellcrank is a solid one-piece bellcrank with no 
rivets, no further action is required by this paragraph.
    (3) If the bellcrank assembly has P/N 252T2118-1, 252T2118-2, or 
252T2118-3, and has shear rivets, before further flight, do the 
action specified in either paragraph (j)(3)(i) or (j)(3)(ii) of this 
AD, in accordance with the Accomplishment Instructions of Boeing 
Service Bulletin 767-27-0186, dated June 25, 2007 (for Model 767-
200, -300, and -300F series airplanes); or 767-27-0187, dated June 
25, 2007 (for Model 767-400ER series airplanes); except as provided 
by paragraph (n) of this AD.
    (i) Rework the existing bellcrank to replace the shear rivets 
with solid rivets.
    (ii) Install a new, solid one-piece (no rivets) bellcrank 
assembly having P/N 252T2118-6.

(k) New Repetitive Functional Test (Pogo Check)

    (1) For airplanes having line numbers 1 through 901 inclusive: 
Before further flight after doing the inspection and applicable 
corrective actions required by paragraph (j) of this AD, do a 
functional test (pogo check) on each of the six elevator PCA input 
rod assemblies, in accordance with the Accomplishment Instructions 
of Boeing Service Bulletin 767-27-0186, dated June 25, 2007 (for 
Model 767-200, -300, and -300F series airplanes); or 767-27-0187, 
dated June 25, 2007 (for Model 767-400ER series airplanes).
    (2) For all airplanes: At the latest of the times specified in 
paragraphs (k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD, do a

[[Page 12995]]

functional test (pogo check) on each of the six elevator PCA input 
rod assemblies, in accordance with the Accomplishment Instructions 
of Boeing Service Bulletin 767-27-0200, dated June 25, 2007 (for 
Model 767-200, -300, and -300F series airplanes); or 767-27-0201, 
dated June 27, 2007 (for Model 767-400ER series airplanes). Repeat 
the pogo check thereafter at intervals not to exceed 12,000 flight 
hours.
    (i) Before the accumulation of 12,000 total flight hours.
    (ii) Within 12,000 flight hours after completion of the most 
recent pogo check.
    (iii) Within 6,000 flight hours after the effective date of this 
AD.
    (3) If any elevator PCA input rod assembly fails to meet any 
functional test requirement of this AD, before further flight, 
replace the elevator PCA input rod assembly with a new or 
serviceable assembly, or overhaul the elevator PCA input rod 
assembly, in accordance with the applicable service information 
identified in paragraphs (k)(3)(i) and (k)(3)(ii) of this AD, except 
as provided by paragraph (n) of this AD.
    (i) For replacing or overhauling the assembly on Model 767-200, 
-300, and -300F airplanes: Use Boeing Service Bulletin 767-27-0186, 
dated June 25, 2007; or 767-27-0200, dated June 25, 2007; as 
applicable.
    (ii) For replacing or overhauling the assembly on Model 767-
400ER airplanes: Use Boeing Service Bulletin 767-27-0187, dated June 
25, 2007; or 767-27-0201, dated June 27, 2007; as applicable.

(l) New Elevator PCA Check (Mis-Rig Check)

    (1) For airplanes having line numbers 1 through 901 inclusive: 
Before further flight after doing the actions required by paragraphs 
(j) and (k) of this AD, do a check of the elevator PCA rigging, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 767-27-0186, dated June 25, 2007 (for Model 767-200, -300, 
and -300F series airplanes); or 767-27-0187, dated June 25, 2007 
(for Model 767-400ER series airplanes).
    (2) For all airplanes: At the latest of the times specified in 
paragraphs (l)(2)(i), (l)(2)(ii), and (l)(2)(iii) of this AD, do a 
check of the elevator PCA rigging, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 767-27-0202, 
Revision 1, dated February 21, 2008 (for Model 767-200, -300, and -
300F series airplanes); or 767-27-0203, Revision 1, dated February 
21, 2008 (for Model 767-400ER series airplanes). Repeat the mis-rig 
check thereafter at intervals not to exceed 6,000 flight hours.
    (i) Before the accumulation 6,000 total flight hours.
    (ii) Within 6,000 flight hours after the completion of the most 
recent mis-rig check, or after completion of the most recent 
bellcrank repetitive check, as specified in Boeing Alert Service 
Bulletin 767-27A0168.
    (iii) Within 6,000 flight hours after the effective date of this 
AD.
    (3) If a mis-rig condition is found, before further flight, 
adjust the PCA input rod assemblies and do a structural inspection 
for damage, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 767-27-0202, Revision 1, dated February 21, 
2008 (for Model 767-200, -300, and -300F airplanes); or 767-27-0203, 
Revision 1, dated February 21, 2008 (for Model 767-400ER airplanes). 
If any damage is found during any structural inspection, before 
further flight, repair in accordance with a method approved by the 
Manager, Seattle Aircraft Certification Office (ACO), FAA. 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.

(m) Terminating Action

    Accomplishment of the requirements of paragraphs (j), (k), and 
(l) of this AD terminates the requirements of paragraphs (g), (h), 
and (i) of this AD.

(n) Service Bulletin Exception

    Where Boeing Service Bulletins 767-27-0186 and 767-27-0187, both 
dated June 25, 2007, specify the use of grease BMS 3-24, this AD 
allows the alternate use of grease BMS 3-33.

(o) Method of Compliance for Paragraph (k) of AD 2007-24-08, Amendment 
39-15274 (72 FR 67236, November 28, 2007)

    For airplanes identified in paragraphs (o)(1) and (o)(2) of this 
AD: Doing the actions required by paragraphs (j), (k), and (l) of 
this AD is acceptable for compliance with the actions required by 
paragraph (k) of AD 2007-24-08, Amendment 39-15274 (72 FR 67236, 
November 28, 2007).
    (1) Group 1, Configuration 2, airplanes identified in Boeing 
Special Attention Service Bulletin 767-27-0197, Revision 1, dated 
July 19, 2007.
    (2) Group 1, Configuration 1, airplanes identified in Boeing 
Special Attention Service Bulletin 767-27-0198, Revision 1, dated 
July 19, 2007.

(p) Parts Installation Prohibition

    As of the effective date of this AD, no person may install a 
bellcrank assembly, P/N 252T2118-1, 252T2118-2, or 252T2118-3, on 
any airplane.

(q) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (l) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Service Bulletin 767-27-0202 
(for Model 767-200, -300, and -300F airplanes) or 767-27-0203, (for 
Model 767-400ER airplanes), both dated June 25, 2007.

(r) 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.
    (4) AMOCs approved previously in accordance with AD 2001-04-09, 
Amendment 39-12128 (66 FR 13227, March 5, 2001), are approved as 
AMOCs for the corresponding requirements of this AD.

(s) Related Information

    (1) For more information about this AD, contact Marie Hogestad, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; phone: 425-917-6418; fax: (425) 917-6590; email: 
marie.hogestad@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 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.

    Issued in Renton, Washington, on February 13, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-04338 Filed 2-25-13; 8:45 am]
BILLING CODE 4910-13-P