[Federal Register Volume 79, Number 17 (Monday, January 27, 2014)]
[Rules and Regulations]
[Pages 4269-4274]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-01433]
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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;
Amendment 39-17699; AD 2013-25-03]
RIN 2120-AA64
Airworthiness Directives; the Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are superseding Airworthiness Directives (ADs) AD 2000-17-
05 and AD 2001-04-09 for all the Boeing Company Model 767 airplanes. AD
2000-17-05 required 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. AD 2001-04-09 required 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 for the elevator PCA, and follow-on actions if
necessary. Since we issued ADs 2000-17-05 and 2001-04-09, a terminating
modification has been designed. This new AD requires 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 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.
DATES: This AD is effective March 3, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 3,
2014.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
November 28, 2007 (72 FR 67236, November 28, 2007).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of March
20, 2001 (66 FR 13227, March 5, 2001).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
September 11, 2000 (65 FR 51754, August 25, 2000).
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at 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 Docket Management Facility, U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT: 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: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede 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). ADs 2000-17-05 and 2001-04-09 applied to the specified
products. The NPRM published in the Federal Register on February 26,
2013 (78 FR 12991). The NPRM proposed to continue to require a
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. The
NPRM also proposed to continue to require repetitive testing of the
elevator control system to determine if an elevator PCA is rigged
incorrectly due to failed shear rivets in a bellcrank assembly of the
elevator PCA, and follow-on actions if necessary. The NPRM also
proposed to 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.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(78 FR 12991, February 26, 2013) and the FAA's response to each
comment.
Request To Withdraw the NPRM (78 FR 12991, February 26, 2013)
United Airlines (UAL) requested that we withdraw the NPRM (78 FR
12991, February 26, 2013). UAL stated that there may be no benefit to
superseding AD 2001-04-09, Amendment 39-12128 (66 FR 13227, March 5,
2001), because current actions provide an equivalent level of safety.
UAL stated that, as an alternative method of compliance (AMOC) to AD
2001-04-09, it is presently accomplishing the actions described in the
following service bulletins. UAL stated that it is effectively
complying with the NPRM, and indicated other airlines may be as well.
Boeing Service Bulletin 767-27-0186, dated June 25, 2007.
Boeing Service Bulletin 767-27-0187, dated June 25, 2007.
Boeing Service Bulletin 767-27-0200, dated June 25, 2007.
Boeing Service Bulletin 767-27-0201, dated June 27, 2007.
Boeing Service Bulletin 767-27-0202, Revision 1, dated
February 21, 2008.
[[Page 4270]]
Boeing Service Bulletin 767-27-0203, Revision 1, dated
February 21, 2008.
We disagree with the commenter's request to withdraw the NPRM (78
FR 12991, February 26, 2013). 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 considered interim actions. This final rule
specifies a terminating modification that will further reduce the
probability of the unsafe condition identified in those ADs, which
includes installation of solid elevator PCA bellcranks or bellcranks
with solid rivets. In addition to this terminating modification, this
final rule requires new repetitive testing of the modified system,
including repetitive testing of the elevator PCA input rod assemblies
(pogo check) and repetitive checks of the elevator PCA rigging.
As UAL indicated, we approved accomplishment of the service
information required by this final rule as AMOCs to accomplishing the
repetitive testing required by paragraph (a) of AD 2001-04-09,
Amendment 39-12128 (66 FR 13227, March 5, 2001). These were global
AMOCs; therefore, we have no way of determining the level of airline
incorporation. Airlines similar to UAL, which are presently
accomplishing the actions described in Boeing Service Bulletins 767-27-
0186, 767-27-0187, and 767-27-0200, all dated June 25, 2007; 767-27-
0201, dated June 27, 2007; and 767-27-0202 and 767-27-0203, both
Revision 1, both dated February 21, 2008; as applicable; as AMOCs to AD
2001-04-09, can take credit for work already accomplished as specified
in paragraph (f) of this final rule and are already doing the
repetitive actions required by this AD. No change has been made to this
final rule in this regard.
Request To Allow Credit for Previous Actions
Boeing requested that we provide credit for the actions required by
paragraph (j) of the NPRM (78 FR 12991, February 26, 2013), if those
actions were performed before the effective date of this AD using
Boeing Service Bulletin 767-27-0186 or 767-27-0187, both dated June 25,
2007, and it is shown that the service information has been
incorporated by doing a records check.
We find that clarification is necessary. Paragraph (f) of this AD
states to comply with this AD within the compliance times specified,
unless already done. For paragraph (j) of this AD, there is no more
work required for operators who have already accomplished the actions
in Boeing Service Bulletin 767-27-0186 or 767-27-0187, both dated June
25, 2007. No change has been made to this final rule in this regard.
Request To Insert a Phrase in Paragraph (k)(1) of the NPRM (78 FR
12991, February 26, 2013)
ABX Air (ABX) requested that paragraph (k)(1) of the NPRM (78 FR
12991, February 26, 2013) be revised by inserting the phrase, ``Unless
the function check (pogo check) specified by paragraph (k)(2) of this
AD was previously accomplished.'' ABX stated that paragraph (k)(1) of
the NPRM proposed to require accomplishment of the pogo check in
accordance with Boeing Service Bulletin 767-27-0186, dated June 25,
2007, before further flight after doing the inspection and applicable
corrective actions proposed by paragraph (j) of the NPRM. ABX stated
that if the pogo check was accomplished previously in accordance with
Boeing Service Bulletin 767-27-0200, dated June 25, 2007, then the pogo
check proposed by paragraph (k)(1) of the NPRM is not necessary.
ABX further stated that the pogo check specified in Boeing Service
Bulletins 767-27-0186 and 767-27-0200, both dated June 25, 2007, are
equivalent, and if each input control rod assembly passed the pogo
check inspection, or was overhauled or replaced in accordance with
paragraph (k)(2) of the NPRM (78 FR 12991, February 26, 2013), then the
repetitive pogo check limit of 12,000 flight hours will provide
protection against input control rod assembly malfunction. ABX stated
that requiring accomplishment of the pogo check concurrently with the
bellcrank assembly inspection/modification will provide no safety
benefit if the inspections specified in paragraph (k)(2) of the NPRM
are in place.
We disagree with revising paragraph (k)(1) of this final rule as
requested. Boeing Service Bulletins 767-27-0186 and 767-27-0187, both
dated June 25, 2007 (referenced in paragraph (j) of this AD), are
applicable to line numbers 1 through 901. An equivalent change was made
during production for line numbers 902 and subsequent. As ABX stated,
Boeing Service Bulletins 767-27-0186 and 767-27-0187, both dated June
25, 2007, include the same testing provided in Boeing Service Bulletins
767-27-0200, dated June 25, 2007; 767-27-0201, dated June 27, 2007; and
767-27-0202 and 767-27-0203, both Revision 1, both dated February 21,
2008.
However, for line numbers 1 through 901, the initial checks (pogo
and mis-rig) must be completed following the modification of the system
and must be repeated at the repetitive inspection intervals provided in
paragraphs (k)(2) and (l)(2) of this AD. Since paragraphs (k)(1) and
(l)(1) of this AD are the initial checks for these airplanes, and the
intent is to do all of the actions specified in Boeing Service
Bulletins 767-27-0186 and 767-27-0187, both dated June 25, 2007, at the
time of modification, we disagree with making the requested change. No
change has been made to this final rule in this regard.
Request To Add Exception to Service Information
Boeing requested that we add an exception to allow operators to
omit Step 5 of Work Packages 1 and 2 of Boeing Service Bulletins 767-
27-0186 and 767-27-0187, both dated June 25, 2007. Boeing stated that
Step 4 of Work Packages 1 and 2 of Boeing Service Bulletins 767-27-0186
and 767-27-0187, both dated June 25, 2007, states ``Install elevator
PCA input linkage. Refer to 767 AMM 27-31-06 as an accepted
procedure.'' Boeing stated that AMM 27-31-06 of the Boeing Aircraft
Maintenance Manual requires adjustment of the PCA input rods per Task
27-31-00, which adjusts the input rods for each elevator PCA to make
sure that the elevator aligns to the index plate. Boeing stated that
Step 5 of Work Packages 1 and 2 of Boeing Service Bulletins 767-27-0186
and 767-27-0187, both dated June 25, 2007, states, ``Do the elevator
PCA Mis-Rig test. Refer to 767 AMM 27-31-00 as an accepted procedure.''
Boeing stated that the PCA input rod adjustment per AMM 27-31-00 is a
precise rigging of the elevator PCA input rods. Boeing stated that a
subsequent mis-rig test, which tests for a gross mis-rig of the system,
is redundant and has no effect on correcting the unsafe condition.
We agree with adding an exception in this final rule as requested.
We re-designated paragraph (n) of the NPRM (78 FR 12991, February 26,
2013) as paragraph (n)(1) of this final rule. We also added new
paragraph (n)(2) to this final rule to specify that for airplanes on
which an adjustment of the PCA input rods has been done as specified in
AMM 27-31-00 of the Boeing 767 Aircraft Maintenance Manual during the
accomplishment of Step 3.B.4 of Work Packages 1 and 2 of Boeing Service
Bulletins 767-27-0186 and 767-27-0187, both dated June 25, 2007, Step
3.B.5 of Work Packages 1 and 2 of Boeing Service Bulletins 767-27-0186
and 767-27-0187, both dated June 25, 2007, is not required. We have
also
[[Page 4271]]
added a reference to paragraph (n)(2) in paragraph (l)(1) of this final
rule.
Clarification of NPRM (78 FR 12991, February 26, 2013)
The preamble of the NPRM (78 FR 12991, February 26, 2013) included
a table identifying revised paragraph identifiers. The second line of
the table stated that paragraph (b) of AD 2000-17-05, Amendment 39-
11879 (65 FR 51754, August 25, 2000), corresponds to paragraph (g)(4)
of the NPRM. We did not retain paragraph (b) of AD 2000-17-05;
therefore, there is no corresponding paragraph (g)(4) in the NPRM.
Since this table is not included in the final rule, no change has been
made to this final rule in this regard.
Additional Change Made to This AD
Certain text in paragraph (h) of the NPRM (78 FR 12991, February
26, 2013) has been redesignated as Note 1 to paragraph (h) in this
final rule, since that text is explanatory only.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 12991, February 26, 2013) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 12991, February 26, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 415 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts U.S. Cost on U.S.
Action Labor cost cost Airplanes Cost per product operators
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Functional check of the shear 4 work-hours x $0 330 $340............. $112,200.
rivets (actions retained from $85 per hour =
AD 2000-17-05, Amendment 39- $340.
11879 (65 FR 51754, August 25,
2000)).
Repetitive inspection of 2 work-hours x 0 335 $170 per $56,950 per
bellcrank assemblies (actions $85 per hour = inspection cycle. inspection
retained from AD 2001-04-09, $170 per cycle.
Amendment 39-12128 (66 FR inspection cycle.
13227, March 5, 2001)).
Inspection of elevator PCA 23 work-hours x 0 390 $1,955........... $762,450.
bellcrank assemblies, $85 per hour =
functional test (pogo check), $1,955.
and elevator mis-rig check
(new actions for Model 767
airplanes having line numbers
1-901).
Repetitive functional test 32 work-hours x 0 415 $2,720 per $1,128,800 per
(pogo check) (new action for $85 per hour = inspection cycle. inspection
all Model 767 airplanes). $2,720 per cycle.
inspection cycle.
Repetitive elevator mis-rig 2 work-hours x 0 415 $170 per $70,550 per
check (new action for all $85 per hour = inspection cycle. inspection
Model 767 airplanes). $170 per cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs or
replacements that will be required based on the results of the
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 will 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 AD.
According to the manufacturer, some of the costs of this 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 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),
[[Page 4272]]
(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 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:
2013-25-03 the Boeing Company: Amendment 39-17699; Docket No. FAA-
2013-0095; Directorate Identifier 2011-NM-197-AD.
(a) Effective Date
This AD is effective March 3, 2014.
(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).
(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 this paragraph, paragraph (g)(2), and
paragraph (g)(3) 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), including all subparagraphs, 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. Doing the actions required by
paragraphs (j), (k), and (l) of this AD terminates the requirements
of this paragraph.
Note 1 to paragraph (h) of this AD: 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 is 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),
which is not incorporated by reference in 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 this paragraph, paragraph (i)(1), and paragraph (i)(2) 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.
[[Page 4273]]
(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
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) Except as provided by paragraph (n)(2) of this AD, 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, dated November 20, 2000.
(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 Exceptions
(1) 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.
(2) For airplanes on which an adjustment of the PCA input rods
has been done as specified in Boeing 767 AMM 27-31-00 during the
accomplishment of Step 3.B.4 of Work Packages 1 and 2 of Boeing
Service Bulletins 767-27-0186 and 767-27-0187, both dated June 25,
2007: Accomplishment of the actions specified in Step 3.B.5 of Work
Package 1 and 2 of Boeing Service Bulletins 767-27-0186 and 767-27-
0187, both dated June 25, 2007, is not required by this AD.
(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, which are not
incorporated by reference in this AD.
(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 paragraph (s) 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.
[[Page 4274]]
(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 for 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:
[email protected].
(2) Service information identified in this AD that is not
incorporated by reference in this AD may be obtained at the
addresses specified in paragraphs (t)(7) and (t)(8) of this AD.
(t) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
March 3, 2014.
(i) Boeing Service Bulletin 767-27-0186, dated June 25, 2007.
(ii) Boeing Service Bulletin 767-27-0187, dated June 25, 2007.
(iii) Boeing Service Bulletin 767-27-0200, dated June 25, 2007.
(iv) Boeing Service Bulletin 767-27-0201, dated June 27, 2007.
(v) Boeing Service Bulletin 767-27-0202, Revision 1, dated
February 21, 2008.
(vi) Boeing Service Bulletin 767-27-0203, Revision 1, dated
February 21, 2008.
(4) The following service information was approved for IBR on
November 28, 2007 (72 FR 67236, November 28, 2007).
(i) Boeing Special Attention Service Bulletin 767-27-0197,
Revision 1, dated July 19, 2007.
(ii) Boeing Special Attention Service Bulletin 767-27-0198,
Revision 1, dated July 19, 2007.
(5) The following service information was approved for IBR on
March 20, 2001 (66 FR 13227, March 5, 2001).
(i) Boeing Alert Service Bulletin 767-27A0168, dated November
21, 2000.
(ii) Boeing Alert Service Bulletin 767-27A0169, dated November
21, 2000.
(6) The following service information was approved for IBR on
September 11, 2000 (65 FR 51754, August 25, 2000).
(i) Boeing Alert Service Bulletin 767-27A0166, dated August 17,
2000.
(ii) Reserved.
(7) 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.
(8) You may view this service information at 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.
(9) 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 December 4, 2013.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-01433 Filed 1-24-14; 8:45 am]
BILLING CODE 4910-13-P