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Published 2014-01-27 · Federal Register document 2014-01433

Airworthiness Directives; the Boeing Company Airplanes

Publication 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.

Why this record is shown

Source: Federal Register annual FAA metadata. Acquired 2026-09-03T22:23:45.694519+00:00. The title, summary and date are source facts.

Source revision
federal_register_ad_metadata_2014-642efe379108139d
Source row
results[13]
Raw source SHA-256
642efe379108139d70cbf0492188bfdaee07f4da1173b6bc01335f4de404a707

Final-rule publication

Recorded publication clauses

AD identifier printed in this edition
2013-25-03
Effective date printed in this edition
2014-03-03
Read 20 complete recorded clauses
Effective Date
(a) Effective Date

    This AD is effective March 3, 2014.

Exact source excerpt. Text positions 21570–21631, end exclusive, in the original decoded publication. SHA-256: 3217c287609989cd8797e45f11f7a97735b2ef89dd973004aeb178d7a655be50

Affected ADs
(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).

Exact source excerpt. Text positions 21631–21894, end exclusive, in the original decoded publication. SHA-256: b6677525d190b6959c5214260c07cf28e709ba57471e150871614f1b08890c16

Applicability wording · Applicability
(c) Applicability

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

Exact source excerpt. Text positions 21894–22048, end exclusive, in the original decoded publication. SHA-256: d69ddb3e6bc58131e5b4b258c6f030d7c3166148f1d2c89d9c62575190cf4aea

Subject
(d) Subject

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

Exact source excerpt. Text positions 22048–22175, end exclusive, in the original decoded publication. SHA-256: e31718d6754fa4df8817cb584b3e335c6b14412fe129ec29f29c4b900784a223

Unsafe Condition
(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.

Exact source excerpt. Text positions 22175–22667, end exclusive, in the original decoded publication. SHA-256: 87ac46df244a866372d3ffd23ca86662b42a77111568f16c22acca8e03ab683c

Compliance
(f) Compliance

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

Exact source excerpt. Text positions 22667–22769, end exclusive, in the original decoded publication. SHA-256: 00fbfa31932483f627d0ce0a11cbd2e35e15d9231842b91ac85623ce533912d3

Retained Functional Check
(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.

Exact source excerpt. Text positions 22769–25222, end exclusive, in the original decoded publication. SHA-256: 6e67313eb21465b54def1a202980d80abd1494dcc2a8c2aa3360cedfc26c1ec8

Retained Repetitive Tests
(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.

Exact source excerpt. Text positions 25222–27001, end exclusive, in the original decoded publication. SHA-256: 913e29f40c4aec3ae002f82b16977874dd1b1c8bcab0e8e0b75d77625302a7eb

Retained Follow-On Actions
(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]]

Exact source excerpt. Text positions 27001–28731, end exclusive, in the original decoded publication. SHA-256: 0602c8c946827f9164dc7557a98dd09e60aae6f7f5a6674294d5df0c74188cfd

New Inspection and Modification
(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.

Exact source excerpt. Text positions 28731–30300, end exclusive, in the original decoded publication. SHA-256: db74c110a94af89e6983e20a5e6f5933f7ebe90a4f0cd3c5b87de2f715c0e746

New Repetitive Functional Test (Pogo Check)
(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.

Exact source excerpt. Text positions 30300–32480, end exclusive, in the original decoded publication. SHA-256: 5cec0f1a93bba6a0f084988099ef2fc51b11a333d46926fcba13ac6b48988f81

New Elevator PCA Check (Mis-rig Check)
(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.

Exact source excerpt. Text positions 32480–34689, end exclusive, in the original decoded publication. SHA-256: 3f2e3a8f972e756071bc30971ea726474ccde2ea9739bf5cfc3fdf2923d30aa0

Terminating Action
(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.

Exact source excerpt. Text positions 34689–34870, end exclusive, in the original decoded publication. SHA-256: d3e2fb99c5853b91374a4c1b43bc807d08a5e2e6dbf2d7da6965b88619bbb798

Service Bulletin Exceptions
(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.

Exact source excerpt. Text positions 34870–35553, end exclusive, in the original decoded publication. SHA-256: df2e92f523eb53b1757362347a7b2d665d4d1560b437fbab5eb91a195aa3996e

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

Exact source excerpt. Text positions 35553–36255, end exclusive, in the original decoded publication. SHA-256: eb358faea3be479c395c043614048eb156ce7c5bc9bc721ad4900413c86d01eb

Parts Installation Prohibition
(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.

Exact source excerpt. Text positions 36255–36439, end exclusive, in the original decoded publication. SHA-256: 7f577f141d306e9a97f26f9c9203fad283189111569195c725012001c6d6b3fe

Credit for Previous Actions
(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.

Exact source excerpt. Text positions 36439–36852, end exclusive, in the original decoded publication. SHA-256: 1a828aa57ca06f444e7bd187bc3b5d0adee88e16dd4699bd802d7cc9a482fd5c

Alternative Methods of Compliance (AMOCs)
(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.

Exact source excerpt. Text positions 36852–38254, end exclusive, in the original decoded publication. SHA-256: 95bb1877762205a03f13e1296fd2d68ddbe78d5c1c758a4fd6d048182192f846

Related Information
(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.

Exact source excerpt. Text positions 38254–38757, end exclusive, in the original decoded publication. SHA-256: 4b3a357fc4882013533c2ef543b160a76eb3499b5b6839ba0f206564d3a58037

Material Incorporated by Reference
(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.

Exact source excerpt. Text positions 38757–41213, end exclusive, in the original decoded publication. SHA-256: 0787b8582a2150ec182c34317fdd1da242e6865a1af6654fdf3c78c2bf878290

No replacement link has been established from this edition. The complete historical rule chain and current legal effect remain unknown.

Find all recorded historical references to AD 2013-25-03 · 0 printed reference observations in this pinned collection.

These are observations from one dated publication. Current legal status is unknown; aircraft applicability, installed configuration, compliance and burden require separate evidence. Missing or unparsed conditions remain unknown.

Why these observations are shown

They were extracted offline from the same immutable official HTML source as the complete recorded text. The dated source wording, original text coordinates and exact quote digests are retained. PDF/text agreement and current regulatory effect have not been qualified.

Observation revision: whole-ad-publication-clause-observations-1.0.1. Text SHA-256: 87015ce89c520eea13a8e725220074fb6503dde2c34feddc5bc279b9ac1980c6. Source manifest: 61a4181d3264a32fd5690e2eb0c246b968264a5d1fb7365e900a2e4e6d762429.

Official source · 2014-01-27

Publication text

This is the complete recorded text of this dated publication.

Current legal effect is unknown. Aircraft applicability, installed configuration and compliance require separate evidence. PDF/text agreement has not been evaluated.

Read the complete official publication text
[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]


-----------------------------------------------------------------------

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.
    <bullet> Boeing Service Bulletin 767-27-0186, dated June 25, 2007.
    <bullet> Boeing Service Bulletin 767-27-0187, dated June 25, 2007.
    <bullet> Boeing Service Bulletin 767-27-0200, dated June 25, 2007.
    <bullet> Boeing Service Bulletin 767-27-0201, dated June 27, 2007.
    <bullet> Boeing Service Bulletin 767-27-0202, Revision 1, dated 
February 21, 2008.

[[Page 4270]]

    <bullet> 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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (78 FR 12991, February 26, 2013) for correcting the unsafe 
condition; and
    <bullet> 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
----------------------------------------------------------------------------------------------------------------
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
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