Airworthiness Directives; The Boeing Company Airplanes, 12991-12995 [2013-04338]
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Federal Register / Vol. 78, No. 38 / Tuesday, February 26, 2013 / Proposed Rules
Renton, WA. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on February
11, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–04339 Filed 2–25–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0095; Directorate
Identifier 2011–NM–197–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
AGENCY:
SUMMARY: We propose to supersede two
existing airworthiness directives (AD)
that apply to all The Boeing Company
Model 767 airplanes. One AD currently
requires a functional check of the shear
rivets in all six elevator power control
actuator (PCA) bellcrank assemblies to
determine the condition of the shear
rivets, and replacement or rework of the
bellcrank assemblies if necessary. The
other AD currently requires repetitive
testing of the elevator control system to
determine if an elevator PCA is rigged
incorrectly, and follow-on actions if
necessary. Since we issued those ADs,
a terminating modification has been
designed. This proposed AD would
require an inspection to determine the
part numbers and condition of the
bellcrank assemblies; modification or
replacement of the PCA bellcrank
assembly, if necessary; and a repetitive
functional test and mis-rig check, and
corrective actions if necessary. We are
proposing this AD to prevent continued
operation with yielded or failed shear
rivets in the elevator PCA bellcrank
assemblies, and to prevent certain
failures or jams in the elevator system
from causing a hardover of the elevator
surface, resulting in a significant pitch
upset and possible loss of control of the
airplane.
DATES: We must receive comments on
this proposed AD by April 12, 2013.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
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• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may
review copies of the referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Marie Hogestad, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6418;
fax: 425–917–6590; email:
marie.hogestad@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2013–0095; Directorate Identifier
2011–NM–197–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
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12991
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On August 18, 2000, we issued AD
2000–17–05, Amendment 39–11879 (65
FR 51754, August 25, 2000), for certain
The Boeing Company Model 767–200,
–300, and –300F series airplanes. That
AD requires a one-time functional check
of the shear rivets in all six PCA
bellcrank assemblies to determine the
condition of the shear rivets; and
replacement or rework of the bellcrank
assemblies, if necessary. That AD
resulted from reports that elevator
bellcrank assemblies with failed shear
rivets had been found on three Model
767 airplanes. We issued that AD to
detect and correct any failed or partially
yielded shear rivets of the elevator PCA
bellcrank assemblies. Failure of two
bellcrank assemblies on one side can
result in that single elevator surface
moving to a hardover position,
independent of pilot command,
resulting in a significant pitch upset
recoverable by the crew. Failure of three
bellcrank assemblies on one side could
result in loss of control of the airplane.
On February 21, 2001, we issued AD
2001–04–09, Amendment 39–12128 (66
FR 13227, March 5, 2001), for all The
Boeing Company Model 767 airplanes.
That AD requires repetitive testing of
the elevator control system to determine
if an elevator PCA is rigged incorrectly
due to yielded or failed shear rivets in
a bellcrank assembly of the elevator
PCA, and follow-on actions if necessary.
That AD resulted from reports that
several Model 767 airplanes failed the
one-time functional check of the shear
rivets in the bellcrank assemblies of the
elevator PCA required by AD 2000–17–
05, Amendment 39–11879 (65 FR
51754, August 25, 2000). We issued AD
2001–04–09, Amendment 39–12128 (66
FR 13227, March 5, 2001), to prevent
continued operation with yielded or
failed shear rivets in a bellcrank
assembly of the elevator PCA, which
could result in loss of control of the
airplane.
Actions Since Existing AD 2000–17–05,
Amendment 39–11879 (65 FR 51754,
August 25, 2000); and AD 2001–04–09,
Amendment 39–12128 (66 FR 13227,
March 5, 2001) Issued
The preambles to AD 2000–17–05,
Amendment 39–11879 (65 FR 51754,
August 25, 2000); and AD 2001–04–09,
Amendment 39–12128 (66 FR 13227,
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March 5, 2001); specify that we consider
the requirements ‘‘interim action.’’
Those ADs explain that we might
consider further rulemaking if a
modification is developed, approved,
and available. The manufacturer now
has developed such a modification, and
we have determined that further
rulemaking is indeed necessary; this
proposed AD follows from that
determination.
Relevant Service Information
We reviewed Boeing Service Bulletins
767–27–0186, dated June 25, 2007 (for
Model 767–200, –300, and –300F series
airplanes); and 767–27–0187, dated June
25, 2007 (for Model 767–400ER series
airplanes). This service information
describes procedures for doing a general
visual inspection of the PCA bellcrank
assemblies on each elevator to
determine if the bellcrank assembly has
shear rivets; and installing a solid
elevator PCA bellcrank assembly or
reworking the bellcrank assembly to
replace the shear rivets with solid rivets,
if necessary. This service information
also describes procedures for the initial
test of the elevator PCA input rod
assemblies (pogo check), and
replacement or overhaul if necessary;
and an elevator PCA rigging check.
We also reviewed Boeing Service
Bulletins 767–27–0200, dated June 25,
2007 (for Model 767–200, –300, and
–300F series airplanes); and 767–27–
0201, dated June 27, 2007 (for Model
767–400ER series airplanes). This
service information describes
procedures for repetitive testing of the
elevator PCA input rod assemblies (pogo
check), and replacing or overhauling the
elevator PCA input rod assembly, if
necessary.
We reviewed Boeing Service Bulletins
767–27–0202, Revision 1, dated
February 21, 2008 (for Model 767–200,
–300, and –300F series airplanes); and
767–27–0203, Revision 1, dated
February 21, 2008 (for Model 767–
400ER series airplanes). This service
information describes procedures for
doing repetitive checks of the elevator
PCA rigging, and adjusting the PCA
input rod assemblies and structural
inspection, if necessary.
Amendment 39–12128 (66 FR 13227,
March 5, 2001). This proposed AD
would require an inspection to
determine the part numbers and
condition of the bellcrank assemblies;
modification or replacement of the PCA
bellcrank assembly, if necessary; and
repetitive post-modification testing and
corrective actions, if necessary. This
proposed AD would also require
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Differences Between the Proposed AD
and the Service Information.’’
Other Relevant Rulemaking
Change to Existing AD 2001–04–09 (66
FR 13227, March 5, 2001) and AD
2000–17–05, Amendment 39–11879 (65
FR 51754, August 25, 2000)
AD 2007–24–08, Amendment 39–
15274 (72 FR 67236, November 28,
2007), was issued for Model 767
airplanes. That AD requires repetitive
measurements of the rudder and
elevator freeplay, related investigative
and corrective actions if necessary, and
repetitive lubrications of the rudder and
elevator components. For certain
airplanes, we require concurrent
actions.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would retain
certain requirements of AD 2000–17–05,
Amendment 39–11879 (65 FR 51754,
August 25, 2000); and AD 2001–04–09,
Boeing Commercial Airplanes has
received an Organization Designation
Authorization (ODA). We have revised
this proposed AD to delegate the
authority to approve an alternative
method of compliance for any repair
required by this proposed AD to the
Boeing Commercial Airplanes ODA
rather than a Designated Engineering
Representative (DER).
Since AD 2000–17–05, Amendment
39–11879 (65 FR 51754, August 25,
2000); and AD 2001–04–09,
Amendment 39–12128 (66 FR 13227,
March 5, 2001); were issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
table:
REVISED PARAGRAPH IDENTIFIERS
Corresponding
requirement in this
proposed AD
Requirement in previous AD
Paragraph
Paragraph
Paragraph
Paragraph
(a)
(b)
(a)
(b)
of
of
of
of
AD
AD
AD
AD
2000–17–05, Amendment 39–11879 (65 FR 51754, August 25, 2000) ..................................................
2000–17–05 ...............................................................................................................................................
2001–04–09, Amendment 39–12128 (66 FR 13227, March 5, 2001) .....................................................
2001–04–09 ...............................................................................................................................................
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
In addition, we have revised certain
headings pertaining to restated material
throughout this AD.
Differences Between the Proposed AD
and the Service Information
This proposed AD will allow for an
alternate grease (BMS 3–33) when
accomplishing the actions specified in
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Boeing Service Bulletins 767–27–0186
and 767–27–0187, both dated June 25,
2007.
Although Boeing Service Bulletins
767–27–0202 and 767–27–0203, both
Revision 1, both dated February 21,
2008, do not specify a corrective action
following a structural inspection, this
proposed AD would require operators to
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paragraph
paragraph
paragraph
paragraph
(g).
(g)(4).
(h).
(i).
repair conditions using a method
approved by the FAA.
Costs of Compliance
We estimate that this proposed AD
affects 415 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
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12993
ESTIMATED COSTS
U.S.
airplanes
Labor cost
Functional check of the shear
rivets (existing requirement for
AD 2000–17–05, Amendment
39–11879 (65 FR 51754, August 25, 2000)).
Repetitive inspection of
bellcrank assemblies (existing
requirement for AD 2001–04–
09, Amendment 39–12128 (66
FR 13227, March 5, 2001)).
Inspection of elevator PCA
bellcrank assemblies, functional test (pogo check), and
elevator mis-rig check (new
proposed actions for Model
767 airplanes having line
numbers 1–901).
Repetitive functional test (pogo
check) (new proposed action
for all Model 767 airplanes).
Repetitive elevator mis-rig check
(new proposed action for all
Model 767 airplanes).
4 work-hours × $85 per hour =
$340.
$0
330
$340 ................
$112,200.
2 work-hours × $85 per hour =
$170 per inspection cycle.
0
335
$170 per inspection
cycle.
$56,950 per inspection
cycle.
23 work-hours × $85 per hour =
$1,955.
0
390
$1,955 .............
$762,450.
32 work-hours × $85 per hour =
$2,720 per inspection cycle.
0
415
$1,128,800 per inspection
cycle.
2 work-hours × $85 per hour =
$170 per inspection cycle.
0
415
$2,720 per inspection
cycle.
$170 per inspection
cycle.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
We estimate the following costs to do
any necessary repairs or replacements
that would be required based on the
results of the proposed inspection, tests,
and checks. We have no way of
determining the number of aircraft that
might need these repairs or
replacements.
We estimate that reworking the
bellcrank assembly would take about 6
work-hours, for a labor cost of $510 per
airplane; however, we have no
definitive data to determine the cost of
parts required. We have received no
definitive data that would enable us to
provide a cost estimate for replacing or
overhauling the elevator PCA input rod
assembly, adjusting the elevator PCA
input rod assemblies, and doing
structural inspections specified in this
proposed AD.
According to the manufacturer, some
of the costs of this proposed AD might
be covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
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Parts cost
Cost per
product
Action
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.
Cost on U.S. operators
$70,550 per inspection
cycle.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directives (ADs)
2000–17–05, Amendment 39–11879 (65
FR 51754, August 25, 2000); and 2001–
04–09, Amendment 39–12128 (66 FR
13227, March 5, 2001); and adding the
following new AD:
■
The Boeing Company: Docket No. FAA–
2013–0095; Directorate Identifier 2011–
NM–197–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by April 12, 2013.
(b) Affected ADs
This AD supersedes AD 2000–17–05,
Amendment 39–11879 (65 FR 51754, August
25, 2000); and AD 2001–04–09, Amendment
39–12128 (66 FR 13227, March 5, 2001). This
AD affects AD 2007–24–08, Amendment 39–
15274 (72 FR 67236, November 28, 2007).
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(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.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Functional Check
This paragraph restates the requirements of
paragraph (a) of AD 2000–17–05,
Amendment 39–11879 (65 FR 51754, August
25, 2000). For Model 767–200, –300, and
–300F series airplanes, line numbers 1
through 800 inclusive: Within 30 days after
September 11, 2000 (the effective date AD
2000–17–05), perform a functional check of
one shear rivet in all six elevator PCA
bellcrank assemblies to determine the
condition of the shear rivets, in accordance
with Paragraph 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–27A0166, dated August 17, 2000. Doing
the actions required by paragraphs (j), (k),
and (l) of this AD terminates the
requirements of paragraph (g) of this AD.
(1) If all penetration depths, when
measured per Figure 2 of Boeing Alert
Service Bulletin 767–27A0166, dated August
17, 2000, are 0.50 inch or more, no further
action is required by paragraph (g) of this AD.
(2) If any penetration depth, when
measured per Figure 2 of Boeing Alert
Service Bulletin 767–27A0166, dated August
17, 2000, is 0.35 inch or more, but less than
0.50 inch, rework or replace the bellcrank
assembly with a new or serviceable bellcrank
assembly within 400 flight hours after
accomplishing the functional check. After
installation of a new or serviceable bellcrank
assembly, and prior to further flight, repeat
the functional check of all the bellcrank
assemblies to make sure the rivets are still in
good condition (as specified in Boeing Alert
Service Bulletin 767–27A0166, dated August
17, 2000) after installation, in accordance
with Figure 2 of Boeing Alert Service
Bulletin 767–27A0166, dated August 17,
2000.
(3) If any penetration depth, when
measured per Figure 2 of Boeing Alert
Service Bulletin 767–27A0166, dated August
17, 2000, is less than 0.35 inch, prior to
further flight, rework or replace the bellcrank
assembly with a new or serviceable bellcrank
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assembly. After installation of a new or
serviceable bellcrank assembly, and prior to
further flight, repeat the functional check of
all the bellcrank assemblies to make sure the
rivets are still in good condition (as specified
in Boeing Alert Service Bulletin 767–
27A0166, dated August 17, 2000) after
installation, in accordance with Figure 2 of
Boeing Alert Service Bulletin 767–27A0166,
dated August 17, 2000.
(h) Retained Repetitive Tests
This paragraph restates the requirements of
paragraph (a) of AD 2001–04–09,
Amendment 39–12128 (66 FR 13227, March
5, 2001), with revised provisions for
repetitive tests. For all airplanes: Within 90
days after March 20, 2001 (the effective date
of AD 2001–04–09), perform a test of the
elevator PCA bellcranks to determine if an
elevator PCA is rigged incorrectly due to
yielded or failed shear rivets in a bellcrank
assembly, in accordance with Boeing Alert
Service Bulletin 767–27A0168 (for Model
767–200, –300, and –300F series airplanes) or
767–27A0169 (for Model 767–400ER series
airplanes), both dated November 21, 2000.
Repeat the test thereafter at least every 400
flight hours. As of March 20, 2001 (the
effective date of AD 2001–04–09), and until
the accomplishment of the actions required
by paragraphs (j), (k), and (l) of this AD, as
applicable. Accomplishment of the repetitive
tests required by paragraph (h) of this AD are
acceptable for compliance with the
functional check of the elevator system
required by a certification maintenance
requirement (CMR) that is documented as
Item Number 27–31–00–5B in the Boeing 767
Maintenance Planning Document (MPD).
Doing the actions required by paragraphs (j),
(k), and (l) of this AD terminates the
requirements of paragraph (h) of this AD.
After accomplishment of the actions required
by paragraphs (j), (k), and (l) of this AD,
accomplishment of the repetitive tests
required by paragraph (h) of this AD are not
acceptable for compliance with the
functional check of the elevator system
required by a CMR that is documented as
Item Number 27–31–00–5B in the Boeing 767
MPD.
(i) Retained Follow-On Actions
This paragraph restates the requirements of
paragraph (b) of AD 2001–04–09,
Amendment 39–12128 (66 FR 13227, March
5, 2001). For all airplanes: If an elevator PCA
is determined to be rigged incorrectly during
any test required by paragraph (h) of this AD,
before further flight, do a one-time inspection
to measure penetration depth of the shear
rivets of all three elevator bellcrank
assemblies of the affected elevator surface, in
accordance with Boeing Alert Service
Bulletin 767–27A0168 (for Model 767–200,
–300, and –300F series airplanes) or 767–
27A0169 (for Model 767–400ER series
airplanes), both dated November 21, 2000.
Doing the actions required by paragraphs (j),
(k), and (l) of this AD terminates the
requirements of paragraph (i) of this AD.
(1) If the measured penetration depth of the
shear rivets on all bellcrank assemblies is
0.50 inch or more: Before further flight, rerig the elevator PCA correctly, in accordance
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with Boeing Alert Service Bulletin 767–
27A0168 (for Model 767–200, –300, and
–300F series airplanes) or 767–27A0169 (for
Model 767–400ER series airplanes), both
dated November 21, 2000.
(2) If the measured shear rivet penetration
depth on any single bellcrank assembly is
less than 0.50 inch: Before further flight,
repair the bellcrank assembly by replacing
the shear rivets or replace the bellcrank
assembly, and reassemble and re-rig the
elevator control system, in accordance with
Boeing Alert Service Bulletin 767–27A0168
(for Model 767–200, –300, and –300F series
airplanes) or 767–27A0169 (for Model 767–
400ER series airplanes), both dated
November 21, 2000.
(j) New Inspection and Modification
For airplanes having line numbers 1
through 901 inclusive: Within 72 months
after the effective date of this AD, do a
general visual inspection of the three PCA
bellcrank assemblies on each elevator to
determine the part numbers (P/Ns) of the
bellcrank assemblies and to determine
whether the bellcrank assembly has shear
rivets, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 767–27–0186, dated June 25,
2007 (for Model 767–200, –300, and –300F
series airplanes); or 767–27–0187, dated June
25, 2007 (for Model 767–400ER series
airplanes).
(1) If the bellcrank assembly has P/N
252T2118–4 or 252T2118–5, and has solid
rivets, no further action is required by this
paragraph.
(2) If the bellcrank is a solid one-piece
bellcrank with no rivets, no further action is
required by this paragraph.
(3) If the bellcrank assembly has P/N
252T2118–1, 252T2118–2, or 252T2118–3,
and has shear rivets, before further flight, do
the action specified in either paragraph
(j)(3)(i) or (j)(3)(ii) of this AD, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 767–27–0186, dated
June 25, 2007 (for Model 767–200, –300, and
–300F series airplanes); or 767–27–0187,
dated June 25, 2007 (for Model 767–400ER
series airplanes); except as provided by
paragraph (n) of this AD.
(i) Rework the existing bellcrank to replace
the shear rivets with solid rivets.
(ii) Install a new, solid one-piece (no rivets)
bellcrank assembly having P/N 252T2118–6.
(k) New Repetitive Functional Test (Pogo
Check)
(1) For airplanes having line numbers 1
through 901 inclusive: Before further flight
after doing the inspection and applicable
corrective actions required by paragraph (j) of
this AD, do a functional test (pogo check) on
each of the six elevator PCA input rod
assemblies, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 767–27–0186, dated June 25,
2007 (for Model 767–200, –300, and –300F
series airplanes); or 767–27–0187, dated June
25, 2007 (for Model 767–400ER series
airplanes).
(2) For all airplanes: At the latest of the
times specified in paragraphs (k)(2)(i),
(k)(2)(ii), and (k)(2)(iii) of this AD, do a
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functional test (pogo check) on each of the
six elevator PCA input rod assemblies, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 767–
27–0200, dated June 25, 2007 (for Model
767–200, –300, and –300F series airplanes);
or 767–27–0201, dated June 27, 2007 (for
Model 767–400ER series airplanes). Repeat
the pogo check thereafter at intervals not to
exceed 12,000 flight hours.
(i) Before the accumulation of 12,000 total
flight hours.
(ii) Within 12,000 flight hours after
completion of the most recent pogo check.
(iii) Within 6,000 flight hours after the
effective date of this AD.
(3) If any elevator PCA input rod assembly
fails to meet any functional test requirement
of this AD, before further flight, replace the
elevator PCA input rod assembly with a new
or serviceable assembly, or overhaul the
elevator PCA input rod assembly, in
accordance with the applicable service
information identified in paragraphs (k)(3)(i)
and (k)(3)(ii) of this AD, except as provided
by paragraph (n) of this AD.
(i) For replacing or overhauling the
assembly on Model 767–200, –300, and
–300F airplanes: Use Boeing Service Bulletin
767–27–0186, dated June 25, 2007; or 767–
27–0200, dated June 25, 2007; as applicable.
(ii) For replacing or overhauling the
assembly on Model 767–400ER airplanes:
Use Boeing Service Bulletin 767–27–0187,
dated June 25, 2007; or 767–27–0201, dated
June 27, 2007; as applicable.
(l) New Elevator PCA Check (Mis-Rig Check)
(1) For airplanes having line numbers 1
through 901 inclusive: Before further flight
after doing the actions required by
paragraphs (j) and (k) of this AD, do a check
of the elevator PCA rigging, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 767–27–0186, dated
June 25, 2007 (for Model 767–200, –300, and
–300F series airplanes); or 767–27–0187,
dated June 25, 2007 (for Model 767–400ER
series airplanes).
(2) For all airplanes: At the latest of the
times specified in paragraphs (l)(2)(i),
(l)(2)(ii), and (l)(2)(iii) of this AD, do a check
of the elevator PCA rigging, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 767–27–0202,
Revision 1, dated February 21, 2008 (for
Model 767–200, –300, and –300F series
airplanes); or 767–27–0203, Revision 1, dated
February 21, 2008 (for Model 767–400ER
series airplanes). Repeat the mis-rig check
thereafter at intervals not to exceed 6,000
flight hours.
(i) Before the accumulation 6,000 total
flight hours.
(ii) Within 6,000 flight hours after the
completion of the most recent mis-rig check,
or after completion of the most recent
bellcrank repetitive check, as specified in
Boeing Alert Service Bulletin 767–27A0168.
(iii) Within 6,000 flight hours after the
effective date of this AD.
(3) If a mis-rig condition is found, before
further flight, adjust the PCA input rod
assemblies and do a structural inspection for
damage, in accordance with the
Accomplishment Instructions of Boeing
VerDate Mar<15>2010
14:55 Feb 25, 2013
Jkt 229001
Service Bulletin 767–27–0202, Revision 1,
dated February 21, 2008 (for Model 767–200,
–300, and –300F airplanes); or 767–27–0203,
Revision 1, dated February 21, 2008 (for
Model 767–400ER airplanes). If any damage
is found during any structural inspection,
before further flight, repair in accordance
with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO),
FAA. For a repair method to be approved, the
repair must meet the certification basis of the
airplane, and the approval must specifically
refer to this AD.
(m) Terminating Action
Accomplishment of the requirements of
paragraphs (j), (k), and (l) of this AD
terminates the requirements of paragraphs
(g), (h), and (i) of this AD.
(n) Service Bulletin Exception
Where Boeing Service Bulletins 767–27–
0186 and 767–27–0187, both dated June 25,
2007, specify the use of grease BMS 3–24,
this AD allows the alternate use of grease
BMS 3–33.
(o) Method of Compliance for Paragraph (k)
of AD 2007–24–08, Amendment 39–15274
(72 FR 67236, November 28, 2007)
For airplanes identified in paragraphs
(o)(1) and (o)(2) of this AD: Doing the actions
required by paragraphs (j), (k), and (l) of this
AD is acceptable for compliance with the
actions required by paragraph (k) of AD
2007–24–08, Amendment 39–15274 (72 FR
67236, November 28, 2007).
(1) Group 1, Configuration 2, airplanes
identified in Boeing Special Attention
Service Bulletin 767–27–0197, Revision 1,
dated July 19, 2007.
(2) Group 1, Configuration 1, airplanes
identified in Boeing Special Attention
Service Bulletin 767–27–0198, Revision 1,
dated July 19, 2007.
(p) Parts Installation Prohibition
As of the effective date of this AD, no
person may install a bellcrank assembly,
P/N 252T2118–1, 252T2118–2, or 252T2118–
3, on any airplane.
(q) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (l) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Service
Bulletin 767–27–0202 (for Model 767–200,
–300, and –300F airplanes) or 767–27–0203,
(for Model 767–400ER airplanes), both dated
June 25, 2007.
(r) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
PO 00000
Frm 00027
Fmt 4702
Sfmt 4702
12995
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane and the
approval must specifically refer to this AD.
(4) AMOCs approved previously in
accordance with AD 2001–04–09,
Amendment 39–12128 (66 FR 13227, March
5, 2001), are approved as AMOCs for the
corresponding requirements of this AD.
(s) Related Information
(1) For more information about this AD,
contact Marie Hogestad, Aerospace Engineer,
Systems and Equipment Branch, ANM–130S,
FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6418; fax: (425) 917–
6590; email: marie.hogestad@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com. You
may review copies of the referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on February
13, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–04338 Filed 2–25–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0093; Directorate
Identifier 2011–NM–109–AD]
RIN 2120–AA64
Airworthiness Directives; Gulfstream
Aerospace LP (Type Certificate
Previously Held by Israel Aircraft
Industries, Ltd.) Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to supersede an
existing airworthiness directive (AD)
that applies to all Gulfstream Aerospace
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]]>Agencies
[Federal Register Volume 78, Number 38 (Tuesday, February 26, 2013)]
[Proposed Rules]
[Pages 12991-12995]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-04338]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0095; Directorate Identifier 2011-NM-197-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede two existing airworthiness directives
(AD) that apply to all The Boeing Company Model 767 airplanes. One AD
currently requires a functional check of the shear rivets in all six
elevator power control actuator (PCA) bellcrank assemblies to determine
the condition of the shear rivets, and replacement or rework of the
bellcrank assemblies if necessary. The other AD currently requires
repetitive testing of the elevator control system to determine if an
elevator PCA is rigged incorrectly, and follow-on actions if necessary.
Since we issued those ADs, a terminating modification has been
designed. This proposed AD would require an inspection to determine the
part numbers and condition of the bellcrank assemblies; modification or
replacement of the PCA bellcrank assembly, if necessary; and a
repetitive functional test and mis-rig check, and corrective actions if
necessary. We are proposing this AD to prevent continued operation with
yielded or failed shear rivets in the elevator PCA bellcrank
assemblies, and to prevent certain failures or jams in the elevator
system from causing a hardover of the elevator surface, resulting in a
significant pitch upset and possible loss of control of the airplane.
DATES: We must receive comments on this proposed AD by April 12, 2013.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Marie Hogestad, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6418; fax: 425-917-6590; email: marie.hogestad@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0095;
Directorate Identifier 2011-NM-197-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On August 18, 2000, we issued AD 2000-17-05, Amendment 39-11879 (65
FR 51754, August 25, 2000), for certain The Boeing Company Model 767-
200, -300, and -300F series airplanes. That AD requires a one-time
functional check of the shear rivets in all six PCA bellcrank
assemblies to determine the condition of the shear rivets; and
replacement or rework of the bellcrank assemblies, if necessary. That
AD resulted from reports that elevator bellcrank assemblies with failed
shear rivets had been found on three Model 767 airplanes. We issued
that AD to detect and correct any failed or partially yielded shear
rivets of the elevator PCA bellcrank assemblies. Failure of two
bellcrank assemblies on one side can result in that single elevator
surface moving to a hardover position, independent of pilot command,
resulting in a significant pitch upset recoverable by the crew. Failure
of three bellcrank assemblies on one side could result in loss of
control of the airplane.
On February 21, 2001, we issued AD 2001-04-09, Amendment 39-12128
(66 FR 13227, March 5, 2001), for all The Boeing Company Model 767
airplanes. That AD requires repetitive testing of the elevator control
system to determine if an elevator PCA is rigged incorrectly due to
yielded or failed shear rivets in a bellcrank assembly of the elevator
PCA, and follow-on actions if necessary. That AD resulted from reports
that several Model 767 airplanes failed the one-time functional check
of the shear rivets in the bellcrank assemblies of the elevator PCA
required by AD 2000-17-05, Amendment 39-11879 (65 FR 51754, August 25,
2000). We issued AD 2001-04-09, Amendment 39-12128 (66 FR 13227, March
5, 2001), to prevent continued operation with yielded or failed shear
rivets in a bellcrank assembly of the elevator PCA, which could result
in loss of control of the airplane.
Actions Since Existing AD 2000-17-05, Amendment 39-11879 (65 FR 51754,
August 25, 2000); and AD 2001-04-09, Amendment 39-12128 (66 FR 13227,
March 5, 2001) Issued
The preambles to AD 2000-17-05, Amendment 39-11879 (65 FR 51754,
August 25, 2000); and AD 2001-04-09, Amendment 39-12128 (66 FR 13227,
[[Page 12992]]
March 5, 2001); specify that we consider the requirements ``interim
action.'' Those ADs explain that we might consider further rulemaking
if a modification is developed, approved, and available. The
manufacturer now has developed such a modification, and we have
determined that further rulemaking is indeed necessary; this proposed
AD follows from that determination.
Relevant Service Information
We reviewed Boeing Service Bulletins 767-27-0186, dated June 25,
2007 (for Model 767-200, -300, and -300F series airplanes); and 767-27-
0187, dated June 25, 2007 (for Model 767-400ER series airplanes). This
service information describes procedures for doing a general visual
inspection of the PCA bellcrank assemblies on each elevator to
determine if the bellcrank assembly has shear rivets; and installing a
solid elevator PCA bellcrank assembly or reworking the bellcrank
assembly to replace the shear rivets with solid rivets, if necessary.
This service information also describes procedures for the initial test
of the elevator PCA input rod assemblies (pogo check), and replacement
or overhaul if necessary; and an elevator PCA rigging check.
We also reviewed Boeing Service Bulletins 767-27-0200, dated June
25, 2007 (for Model 767-200, -300, and -300F series airplanes); and
767-27-0201, dated June 27, 2007 (for Model 767-400ER series
airplanes). This service information describes procedures for
repetitive testing of the elevator PCA input rod assemblies (pogo
check), and replacing or overhauling the elevator PCA input rod
assembly, if necessary.
We reviewed Boeing Service Bulletins 767-27-0202, Revision 1, dated
February 21, 2008 (for Model 767-200, -300, and -300F series
airplanes); and 767-27-0203, Revision 1, dated February 21, 2008 (for
Model 767-400ER series airplanes). This service information describes
procedures for doing repetitive checks of the elevator PCA rigging, and
adjusting the PCA input rod assemblies and structural inspection, if
necessary.
Other Relevant Rulemaking
AD 2007-24-08, Amendment 39-15274 (72 FR 67236, November 28, 2007),
was issued for Model 767 airplanes. That AD requires repetitive
measurements of the rudder and elevator freeplay, related investigative
and corrective actions if necessary, and repetitive lubrications of the
rudder and elevator components. For certain airplanes, we require
concurrent actions.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would retain certain requirements of AD 2000-17-
05, Amendment 39-11879 (65 FR 51754, August 25, 2000); and AD 2001-04-
09, Amendment 39-12128 (66 FR 13227, March 5, 2001). This proposed AD
would require an inspection to determine the part numbers and condition
of the bellcrank assemblies; modification or replacement of the PCA
bellcrank assembly, if necessary; and repetitive post-modification
testing and corrective actions, if necessary. This proposed AD would
also require accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between the Proposed AD and the Service Information.''
Change to Existing AD 2001-04-09 (66 FR 13227, March 5, 2001) and AD
2000-17-05, Amendment 39-11879 (65 FR 51754, August 25, 2000)
Boeing Commercial Airplanes has received an Organization
Designation Authorization (ODA). We have revised this proposed AD to
delegate the authority to approve an alternative method of compliance
for any repair required by this proposed AD to the Boeing Commercial
Airplanes ODA rather than a Designated Engineering Representative
(DER).
Since AD 2000-17-05, Amendment 39-11879 (65 FR 51754, August 25,
2000); and AD 2001-04-09, Amendment 39-12128 (66 FR 13227, March 5,
2001); were issued, the AD format has been revised, and certain
paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in previous AD this proposed AD
------------------------------------------------------------------------
Paragraph (a) of AD 2000-17-05, paragraph (g).
Amendment 39-11879 (65 FR 51754,
August 25, 2000).
Paragraph (b) of AD 2000-17-05........ paragraph (g)(4).
Paragraph (a) of AD 2001-04-09, paragraph (h).
Amendment 39-12128 (66 FR 13227,
March 5, 2001).
Paragraph (b) of AD 2001-04-09........ paragraph (i).
------------------------------------------------------------------------
In addition, we have revised certain headings pertaining to
restated material throughout this AD.
Differences Between the Proposed AD and the Service Information
This proposed AD will allow for an alternate grease (BMS 3-33) when
accomplishing the actions specified in Boeing Service Bulletins 767-27-
0186 and 767-27-0187, both dated June 25, 2007.
Although Boeing Service Bulletins 767-27-0202 and 767-27-0203, both
Revision 1, both dated February 21, 2008, do not specify a corrective
action following a structural inspection, this proposed AD would
require operators to repair conditions using a method approved by the
FAA.
Costs of Compliance
We estimate that this proposed AD affects 415 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
[[Page 12993]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
U.S.
Action Labor cost Parts cost airplanes Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Functional check of the shear 4 work-hours x $85 per $0 330 $340................. $112,200.
rivets (existing requirement for hour = $340.
AD 2000-17-05, Amendment 39-11879
(65 FR 51754, August 25, 2000)).
Repetitive inspection of bellcrank 2 work-hours x $85 per 0 335 $170 per inspection $56,950 per inspection cycle.
assemblies (existing requirement hour = $170 per cycle.
for AD 2001-04-09, Amendment 39- inspection cycle.
12128 (66 FR 13227, March 5,
2001)).
Inspection of elevator PCA 23 work-hours x $85 per 0 390 $1,955............... $762,450.
bellcrank assemblies, functional hour = $1,955.
test (pogo check), and elevator
mis-rig check (new proposed
actions for Model 767 airplanes
having line numbers 1-901).
Repetitive functional test (pogo 32 work-hours x $85 per 0 415 $2,720 per inspection $1,128,800 per inspection cycle.
check) (new proposed action for hour = $2,720 per cycle.
all Model 767 airplanes). inspection cycle.
Repetitive elevator mis-rig check 2 work-hours x $85 per 0 415 $170 per inspection $70,550 per inspection cycle.
(new proposed action for all hour = $170 per cycle.
Model 767 airplanes). inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs or
replacements that would be required based on the results of the
proposed inspection, tests, and checks. We have no way of determining
the number of aircraft that might need these repairs or replacements.
We estimate that reworking the bellcrank assembly would take about
6 work-hours, for a labor cost of $510 per airplane; however, we have
no definitive data to determine the cost of parts required. We have
received no definitive data that would enable us to provide a cost
estimate for replacing or overhauling the elevator PCA input rod
assembly, adjusting the elevator PCA input rod assemblies, and doing
structural inspections specified in this proposed AD.
According to the manufacturer, some of the costs of this proposed
AD might be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directives
(ADs) 2000-17-05, Amendment 39-11879 (65 FR 51754, August 25, 2000);
and 2001-04-09, Amendment 39-12128 (66 FR 13227, March 5, 2001); and
adding the following new AD:
The Boeing Company: Docket No. FAA-2013-0095; Directorate Identifier
2011-NM-197-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by April 12,
2013.
(b) Affected ADs
This AD supersedes AD 2000-17-05, Amendment 39-11879 (65 FR
51754, August 25, 2000); and AD 2001-04-09, Amendment 39-12128 (66
FR 13227, March 5, 2001). This AD affects AD 2007-24-08, Amendment
39-15274 (72 FR 67236, November 28, 2007).
[[Page 12994]]
(c) Applicability
This AD applies to all The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 27, Flight controls.
(e) Unsafe Condition
This AD was prompted by reports of failed shear rivets in the
bellcrank assemblies of the elevator power control actuator (PCA).
We are issuing this AD to prevent continued operation with yielded
or failed shear rivets in the elevator PCA bellcrank assemblies, and
to prevent certain failures or jams in the elevator system from
causing a hardover of the elevator surface, resulting in a
significant pitch upset and possible loss of control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Functional Check
This paragraph restates the requirements of paragraph (a) of AD
2000-17-05, Amendment 39-11879 (65 FR 51754, August 25, 2000). For
Model 767-200, -300, and -300F series airplanes, line numbers 1
through 800 inclusive: Within 30 days after September 11, 2000 (the
effective date AD 2000-17-05), perform a functional check of one
shear rivet in all six elevator PCA bellcrank assemblies to
determine the condition of the shear rivets, in accordance with
Paragraph 3 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 767-27A0166, dated August 17, 2000. Doing the
actions required by paragraphs (j), (k), and (l) of this AD
terminates the requirements of paragraph (g) of this AD.
(1) If all penetration depths, when measured per Figure 2 of
Boeing Alert Service Bulletin 767-27A0166, dated August 17, 2000,
are 0.50 inch or more, no further action is required by paragraph
(g) of this AD.
(2) If any penetration depth, when measured per Figure 2 of
Boeing Alert Service Bulletin 767-27A0166, dated August 17, 2000, is
0.35 inch or more, but less than 0.50 inch, rework or replace the
bellcrank assembly with a new or serviceable bellcrank assembly
within 400 flight hours after accomplishing the functional check.
After installation of a new or serviceable bellcrank assembly, and
prior to further flight, repeat the functional check of all the
bellcrank assemblies to make sure the rivets are still in good
condition (as specified in Boeing Alert Service Bulletin 767-
27A0166, dated August 17, 2000) after installation, in accordance
with Figure 2 of Boeing Alert Service Bulletin 767-27A0166, dated
August 17, 2000.
(3) If any penetration depth, when measured per Figure 2 of
Boeing Alert Service Bulletin 767-27A0166, dated August 17, 2000, is
less than 0.35 inch, prior to further flight, rework or replace the
bellcrank assembly with a new or serviceable bellcrank assembly.
After installation of a new or serviceable bellcrank assembly, and
prior to further flight, repeat the functional check of all the
bellcrank assemblies to make sure the rivets are still in good
condition (as specified in Boeing Alert Service Bulletin 767-
27A0166, dated August 17, 2000) after installation, in accordance
with Figure 2 of Boeing Alert Service Bulletin 767-27A0166, dated
August 17, 2000.
(h) Retained Repetitive Tests
This paragraph restates the requirements of paragraph (a) of AD
2001-04-09, Amendment 39-12128 (66 FR 13227, March 5, 2001), with
revised provisions for repetitive tests. For all airplanes: Within
90 days after March 20, 2001 (the effective date of AD 2001-04-09),
perform a test of the elevator PCA bellcranks to determine if an
elevator PCA is rigged incorrectly due to yielded or failed shear
rivets in a bellcrank assembly, in accordance with Boeing Alert
Service Bulletin 767-27A0168 (for Model 767-200, -300, and -300F
series airplanes) or 767-27A0169 (for Model 767-400ER series
airplanes), both dated November 21, 2000. Repeat the test thereafter
at least every 400 flight hours. As of March 20, 2001 (the effective
date of AD 2001-04-09), and until the accomplishment of the actions
required by paragraphs (j), (k), and (l) of this AD, as applicable.
Accomplishment of the repetitive tests required by paragraph (h) of
this AD are acceptable for compliance with the functional check of
the elevator system required by a certification maintenance
requirement (CMR) that is documented as Item Number 27-31-00-5B in
the Boeing 767 Maintenance Planning Document (MPD). Doing the
actions required by paragraphs (j), (k), and (l) of this AD
terminates the requirements of paragraph (h) of this AD. After
accomplishment of the actions required by paragraphs (j), (k), and
(l) of this AD, accomplishment of the repetitive tests required by
paragraph (h) of this AD are not acceptable for compliance with the
functional check of the elevator system required by a CMR that is
documented as Item Number 27-31-00-5B in the Boeing 767 MPD.
(i) Retained Follow-On Actions
This paragraph restates the requirements of paragraph (b) of AD
2001-04-09, Amendment 39-12128 (66 FR 13227, March 5, 2001). For all
airplanes: If an elevator PCA is determined to be rigged incorrectly
during any test required by paragraph (h) of this AD, before further
flight, do a one-time inspection to measure penetration depth of the
shear rivets of all three elevator bellcrank assemblies of the
affected elevator surface, in accordance with Boeing Alert Service
Bulletin 767-27A0168 (for Model 767-200, -300, and -300F series
airplanes) or 767-27A0169 (for Model 767-400ER series airplanes),
both dated November 21, 2000. Doing the actions required by
paragraphs (j), (k), and (l) of this AD terminates the requirements
of paragraph (i) of this AD.
(1) If the measured penetration depth of the shear rivets on all
bellcrank assemblies is 0.50 inch or more: Before further flight,
re-rig the elevator PCA correctly, in accordance with Boeing Alert
Service Bulletin 767-27A0168 (for Model 767-200, -300, and -300F
series airplanes) or 767-27A0169 (for Model 767-400ER series
airplanes), both dated November 21, 2000.
(2) If the measured shear rivet penetration depth on any single
bellcrank assembly is less than 0.50 inch: Before further flight,
repair the bellcrank assembly by replacing the shear rivets or
replace the bellcrank assembly, and reassemble and re-rig the
elevator control system, in accordance with Boeing Alert Service
Bulletin 767-27A0168 (for Model 767-200, -300, and -300F series
airplanes) or 767-27A0169 (for Model 767-400ER series airplanes),
both dated November 21, 2000.
(j) New Inspection and Modification
For airplanes having line numbers 1 through 901 inclusive:
Within 72 months after the effective date of this AD, do a general
visual inspection of the three PCA bellcrank assemblies on each
elevator to determine the part numbers (P/Ns) of the bellcrank
assemblies and to determine whether the bellcrank assembly has shear
rivets, in accordance with the Accomplishment Instructions of Boeing
Service Bulletin 767-27-0186, dated June 25, 2007 (for Model 767-
200, -300, and -300F series airplanes); or 767-27-0187, dated June
25, 2007 (for Model 767-400ER series airplanes).
(1) If the bellcrank assembly has P/N 252T2118-4 or 252T2118-5,
and has solid rivets, no further action is required by this
paragraph.
(2) If the bellcrank is a solid one-piece bellcrank with no
rivets, no further action is required by this paragraph.
(3) If the bellcrank assembly has P/N 252T2118-1, 252T2118-2, or
252T2118-3, and has shear rivets, before further flight, do the
action specified in either paragraph (j)(3)(i) or (j)(3)(ii) of this
AD, in accordance with the Accomplishment Instructions of Boeing
Service Bulletin 767-27-0186, dated June 25, 2007 (for Model 767-
200, -300, and -300F series airplanes); or 767-27-0187, dated June
25, 2007 (for Model 767-400ER series airplanes); except as provided
by paragraph (n) of this AD.
(i) Rework the existing bellcrank to replace the shear rivets
with solid rivets.
(ii) Install a new, solid one-piece (no rivets) bellcrank
assembly having P/N 252T2118-6.
(k) New Repetitive Functional Test (Pogo Check)
(1) For airplanes having line numbers 1 through 901 inclusive:
Before further flight after doing the inspection and applicable
corrective actions required by paragraph (j) of this AD, do a
functional test (pogo check) on each of the six elevator PCA input
rod assemblies, in accordance with the Accomplishment Instructions
of Boeing Service Bulletin 767-27-0186, dated June 25, 2007 (for
Model 767-200, -300, and -300F series airplanes); or 767-27-0187,
dated June 25, 2007 (for Model 767-400ER series airplanes).
(2) For all airplanes: At the latest of the times specified in
paragraphs (k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD, do a
[[Page 12995]]
functional test (pogo check) on each of the six elevator PCA input
rod assemblies, in accordance with the Accomplishment Instructions
of Boeing Service Bulletin 767-27-0200, dated June 25, 2007 (for
Model 767-200, -300, and -300F series airplanes); or 767-27-0201,
dated June 27, 2007 (for Model 767-400ER series airplanes). Repeat
the pogo check thereafter at intervals not to exceed 12,000 flight
hours.
(i) Before the accumulation of 12,000 total flight hours.
(ii) Within 12,000 flight hours after completion of the most
recent pogo check.
(iii) Within 6,000 flight hours after the effective date of this
AD.
(3) If any elevator PCA input rod assembly fails to meet any
functional test requirement of this AD, before further flight,
replace the elevator PCA input rod assembly with a new or
serviceable assembly, or overhaul the elevator PCA input rod
assembly, in accordance with the applicable service information
identified in paragraphs (k)(3)(i) and (k)(3)(ii) of this AD, except
as provided by paragraph (n) of this AD.
(i) For replacing or overhauling the assembly on Model 767-200,
-300, and -300F airplanes: Use Boeing Service Bulletin 767-27-0186,
dated June 25, 2007; or 767-27-0200, dated June 25, 2007; as
applicable.
(ii) For replacing or overhauling the assembly on Model 767-
400ER airplanes: Use Boeing Service Bulletin 767-27-0187, dated June
25, 2007; or 767-27-0201, dated June 27, 2007; as applicable.
(l) New Elevator PCA Check (Mis-Rig Check)
(1) For airplanes having line numbers 1 through 901 inclusive:
Before further flight after doing the actions required by paragraphs
(j) and (k) of this AD, do a check of the elevator PCA rigging, in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 767-27-0186, dated June 25, 2007 (for Model 767-200, -300,
and -300F series airplanes); or 767-27-0187, dated June 25, 2007
(for Model 767-400ER series airplanes).
(2) For all airplanes: At the latest of the times specified in
paragraphs (l)(2)(i), (l)(2)(ii), and (l)(2)(iii) of this AD, do a
check of the elevator PCA rigging, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 767-27-0202,
Revision 1, dated February 21, 2008 (for Model 767-200, -300, and -
300F series airplanes); or 767-27-0203, Revision 1, dated February
21, 2008 (for Model 767-400ER series airplanes). Repeat the mis-rig
check thereafter at intervals not to exceed 6,000 flight hours.
(i) Before the accumulation 6,000 total flight hours.
(ii) Within 6,000 flight hours after the completion of the most
recent mis-rig check, or after completion of the most recent
bellcrank repetitive check, as specified in Boeing Alert Service
Bulletin 767-27A0168.
(iii) Within 6,000 flight hours after the effective date of this
AD.
(3) If a mis-rig condition is found, before further flight,
adjust the PCA input rod assemblies and do a structural inspection
for damage, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 767-27-0202, Revision 1, dated February 21,
2008 (for Model 767-200, -300, and -300F airplanes); or 767-27-0203,
Revision 1, dated February 21, 2008 (for Model 767-400ER airplanes).
If any damage is found during any structural inspection, before
further flight, repair in accordance with a method approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA. For a
repair method to be approved, the repair must meet the certification
basis of the airplane, and the approval must specifically refer to
this AD.
(m) Terminating Action
Accomplishment of the requirements of paragraphs (j), (k), and
(l) of this AD terminates the requirements of paragraphs (g), (h),
and (i) of this AD.
(n) Service Bulletin Exception
Where Boeing Service Bulletins 767-27-0186 and 767-27-0187, both
dated June 25, 2007, specify the use of grease BMS 3-24, this AD
allows the alternate use of grease BMS 3-33.
(o) Method of Compliance for Paragraph (k) of AD 2007-24-08, Amendment
39-15274 (72 FR 67236, November 28, 2007)
For airplanes identified in paragraphs (o)(1) and (o)(2) of this
AD: Doing the actions required by paragraphs (j), (k), and (l) of
this AD is acceptable for compliance with the actions required by
paragraph (k) of AD 2007-24-08, Amendment 39-15274 (72 FR 67236,
November 28, 2007).
(1) Group 1, Configuration 2, airplanes identified in Boeing
Special Attention Service Bulletin 767-27-0197, Revision 1, dated
July 19, 2007.
(2) Group 1, Configuration 1, airplanes identified in Boeing
Special Attention Service Bulletin 767-27-0198, Revision 1, dated
July 19, 2007.
(p) Parts Installation Prohibition
As of the effective date of this AD, no person may install a
bellcrank assembly, P/N 252T2118-1, 252T2118-2, or 252T2118-3, on
any airplane.
(q) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 767-27-0202
(for Model 767-200, -300, and -300F airplanes) or 767-27-0203, (for
Model 767-400ER airplanes), both dated June 25, 2007.
(r) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane and the approval must
specifically refer to this AD.
(4) AMOCs approved previously in accordance with AD 2001-04-09,
Amendment 39-12128 (66 FR 13227, March 5, 2001), are approved as
AMOCs for the corresponding requirements of this AD.
(s) Related Information
(1) For more information about this AD, contact Marie Hogestad,
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA,
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton,
WA 98057-3356; phone: 425-917-6418; fax: (425) 917-6590; email:
marie.hogestad@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For information on the availability of
this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on February 13, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-04338 Filed 2-25-13; 8:45 am]
BILLING CODE 4910-13-P
