Airworthiness Directives; Boeing Model 767-200 and 767-300 Series Airplanes, 49366-49368 [E8-19363]
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49366
Federal Register / Vol. 73, No. 163 / Thursday, August 21, 2008 / Proposed Rules
the instructions of paragraphs 2.C.(1) through
2.C.(3), and paragraphs 2.D.(1) through
2.D.(3), of the Accomplishment Instructions
of BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53–194,
dated January 10, 2007, except as required by
paragraphs (f)(2), (f)(3), and (f)(4) of this AD.
(2) If any defect is found during the
inspection specified in paragraph (f)(1) of
this AD, before further flight, replace the
affected bolts in accordance with the
Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–194, dated January
10, 2007, except as required by paragraph
(f)(3) and (f)(4) of this AD.
(3) For airplanes on which replacement
parts are not available during the
replacement specified in paragraph (f)(2) of
this AD, do the actions in paragraphs (f)(3)(i)
and (f)(3)(ii) of this AD in accordance with
the Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–194, dated January
10, 2007.
(i) Before further flight, temporarily
reinstall removed oversized bolts, provided
the bolts are serviceable.
(ii) Within 2,000 flight cycles after doing
the inspection required by paragraph (f)(1) of
this AD, replace all temporary oversized bolts
that were installed in accordance with
paragraph (f)(3)(i) of this AD.
(4) Where BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
194, dated January 10, 2007, specifies to
contact BAE Systems (Operations) Limited if
any defect is found in the second oversize
fastener bore, before further flight, contact
BAE Systems (Operations) Limited for repair
instructions and do the repair.
FAA AD Differences
sroberts on PROD1PC70 with PROPOSALS
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send
information to ATTN: Todd Thompson,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone (425)
227–1175; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved if they are approved by the State
of Design Authority (or their delegated
agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
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17:27 Aug 20, 2008
Jkt 214001
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
DEPARTMENT OF TRANSPORTATION
You may send comments 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: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
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
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Tamara L. Anderson, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6421; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Related Information
(h) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2007–
0277, dated November 5, 2007, and BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–194, dated January
10, 2007, for related information.
Issued in Renton, Washington, on August
6, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–19364 Filed 8–20–08; 8:45 am]
BILLING CODE 4910–13–P
[Docket No. FAA–2008–0898; Directorate
Identifier 2007–NM–200–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767–200 and 767–300 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 767–200 and 767–
300 series airplanes. This proposed AD
would require detailed inspections of
the aft pressure bulkhead for damage,
mid-frequency eddy current (MFEC) and
low frequency eddy current (LFEC)
inspections of radial web lap splices,
tear strap splices, and super tear strap
splices for cracking, and corrective
actions if necessary. This AD results
from analysis that indicates fatigue
cracks of the web lap splice, tear strap
splice, or super tear strap splice of the
aft bulkhead are expected to occur on
certain Boeing Model 767–200 and 767–
300 series airplanes. We are proposing
this AD to detect and correct fatigue
cracks of the aft pressure bulkhead,
which could result in rapid
decompression of the passenger
compartment and possible damage or
interference with airplane control
systems that penetrate the bulkhead,
and consequent loss of controllability of
the airplane.
DATES: We must receive comments on
this proposed AD by October 6, 2008.
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ADDRESSES:
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–2008–0898; Directorate Identifier
2007–NM–200–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
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Federal Register / Vol. 73, No. 163 / Thursday, August 21, 2008 / Proposed Rules
substantive verbal contact we receive
about this proposed AD.
sroberts on PROD1PC70 with PROPOSALS
Discussion
We have previously issued AD 2005–
03–11, amendment 39–13967 (70 FR
7174, February 11, 2005). (A correction
of the rule was published in the Federal
Register on March 11, 2005 (70 FR
12119, March 11, 2005).) That AD
applies to certain Boeing Model 767–
200 and 767–300 series airplanes, line
numbers 1 through 175 inclusive. That
AD was prompted by a report of
multiple-site fatigue cracking (multiplesite damage) in two lap splices on the
aft pressure bulkhead of one airplane.
That AD currently requires repetitive
detailed and eddy current inspections of
the aft pressure bulkhead for damage
and cracking, one-time detailed and
high frequency eddy current inspections
of any ‘‘oil can’’ located on the aft
pressure bulkhead for damage and
cracking, and related corrective actions
if necessary.
Since the issuance of that AD,
analysis indicates that fatigue cracks of
the web lap splice, tear strap splice, or
super tear strap splice of the aft
bulkhead are expected to occur on
Boeing Model 767–200 and 767–300
series airplanes having line numbers
176 through 423 inclusive that have
accumulated 35,000 or more total flight
cycles. There have been no reports of
such fatigue cracks on these in-service
airplanes. Such fatigue cracking, if not
corrected, could result in rapid
decompression of the passenger
compartment and possible damage or
interference with airplane control
systems that penetrate the bulkhead,
and consequent loss of controllability of
the airplane.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 767–53A0147, dated
August 16, 2007. The service bulletin
describes procedures for:
• Doing an initial detailed inspection
of the aft pressure bulkhead for damage
such as dents, punctures, nicks, gouges,
cracks, corrosion, and scratches, and
repeating those inspections.
• Doing initial mid-frequency eddy
current (MFEC) and low-frequency eddy
current (LFEC) inspections of the radial
web lap splices, tear strap splices, and
super tear strap splices for cracking, and
repeating those inspections.
• Contacting Boeing for inspection
instructions where inspection is
prevented by a repair common to the
inspection area.
• Doing applicable corrective actions,
which include repairing any damage
that exceeds certain allowable limits,
VerDate Aug<31>2005
17:27 Aug 20, 2008
Jkt 214001
and contacting Boeing for repair
instructions. The service bulletin
specifies the following compliance
times:
• For the initial inspections: 35,000
total flight-cycles, or 18 months or 3,000
flight-cycles after the date of the service
bulletin, whichever occurs first.
• For the repetitive inspections:
Within 3,000 flight-cycles of the initial
inspection, and thereafter at intervals
not to exceed 3,000 flight-cycles.
• For the applicable corrective
actions: Before further flight.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other airplanes of this same
type design. For this reason, we are
proposing this AD, which would require
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Differences Between Proposed Rule
and Service Bulletin.’’
Differences Between Proposed Rule and
Service Bulletin
The service bulletin specifies to
contact the manufacturer for
instructions on how to repair and
inspect certain conditions, but this
proposed AD would require repairing
and inspecting those conditions in one
of the following ways:
• Using a method that we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by an
Authorized Representative for the
Boeing Commercial Airplanes
Delegation Option Authorization
Organization whom we have authorized
to make those findings.
Clarification of Repetitive Inspections
Specified in Service Bulletin
The Accomplishment Instructions of
the service bulletin specifies to only
repeat the inspections if no crack is
found. However, Table 2 of paragraph
1.E, ‘‘Compliance,’’ of the service
bulletin identifies repeat intervals for
the inspections, regardless of inspection
findings. The intent is that the
inspections be repeated for all findings.
Therefore, this proposed AD would
require repetitive inspections at the
applicable repeat intervals listed in
Table 2 of paragraph 1.E.,
‘‘Compliance.’’
Costs of Compliance
There are about 244 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about 84
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49367
airplanes of U.S. registry. The proposed
actions would take about 31 work hours
per airplane, at an average labor rate of
$80 per work hour. Based on these
figures, the estimated cost of the
proposed AD for U.S. operators is
$208,320, or $2,480 per airplane, per
inspection cycle.
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); and
3. 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
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49368
Federal Register / Vol. 73, No. 163 / Thursday, August 21, 2008 / Proposed Rules
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
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
Alternative Methods of Compliance
(AMOCs)
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2008–0898;
Directorate Identifier 2007–NM–200–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by October 6, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 767–
200 and 767–300 series airplanes, certificated
in any category; as identified in Boeing Alert
Service Bulletin 767–53A0147, dated August
16, 2007.
Unsafe Condition
(d) This AD results from analysis that
indicates fatigue cracks of the web lap splice,
tear strap splice, or super tear strap splice of
the aft bulkhead are expected to occur on
certain Boeing Model 767–200 and 767–300
series airplanes. We are proposing this AD to
detect and correct fatigue cracks of the aft
pressure bulkhead, which could result in
rapid decompression of the passenger
compartment and possible damage or
interference with airplane control systems
that penetrate the bulkhead, and consequent
loss of controllability of the airplane.
sroberts on PROD1PC70 with PROPOSALS
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Inspections and Applicable Related
Investigative and Corrective Actions
(f) Except as provided by paragraphs (f)(1)
and (f)(2) of this AD: At the applicable
compliance time and repeat intervals listed
in Tables 1 and 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 767–53A0147, dated August 16,
2007, do detailed inspections of the aft
pressure bulkhead for damage, midfrequency eddy current (MFEC) and lowfrequency eddy current (LFEC) inspections of
radial web lap splices, tear strap splices, and
super tear strap splices for cracking and
applicable corrective actions by
accomplishing all the applicable actions
specified in the Accomplishment
Instructions of the service bulletin.
(1) Where Table 1 of paragraph 1.E.,
‘‘Compliance,’’ of the service bulletin
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17:27 Aug 20, 2008
Jkt 214001
specifies a compliance time after the date on
the service bulletin, this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(2) Where the service bulletin specifies a
compliance time of ‘‘As given by Boeing’’ or
to contact Boeing for the appropriate action,
this AD requires, before further flight,
inspections of the area of repair and repair
of any damaged/cracked part, as applicable,
using a method approved in accordance with
the procedures specified in paragraph (g) of
this AD.
(g)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Tamara L. Anderson, Aerospace Engineer,
Airframe Branch, ANM–120S, 1601 Lind
Avenue, SW., Renton, Washington, telephone
(425) 917–6421; fax (425) 917–6590; has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(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 an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who 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.
Issued in Renton, Washington, on August
8, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–19363 Filed 8–20–08; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0899; Directorate
Identifier 2008–NM–022–AD]
RIN 2120–AA64
Airworthiness Directives; Honeywell
Flight Management Systems (FMSs)
Equipped with Honeywell NZ–2000
Navigation Computers and Honeywell
IC–800 or IC–800E Integrated Avionics
Computers; as Installed on Various
Transport Category Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all
Honeywell FMSs served by Honeywell
NZ–2000 navigation computers and IC–
800 integrated avionics computers. The
existing AD currently requires
identifying affected computers by part
number and software modification level
and revising the Limitations section of
applicable airplane flight manuals to
provide procedures for retaining
optimum position determination and
intended navigation. This proposed AD
would require uploading new software,
which would terminate the existing
requirements. This proposed AD results
from reports of in-flight unannunciated
shifts of computed position in airplanes
with the subject FMS computers. We are
proposing this AD to prevent a shift in
the FMS computed position, which
could result in uncommanded
deviations from the intended flight path
of the airplane and, if those deviations
are undetected by the flight crew,
compromised terrain/traffic avoidance.
DATES: We must receive comments on
this proposed AD by October 6, 2008.
ADDRESSES: You may send comments 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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
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]]>Agencies
[Federal Register Volume 73, Number 163 (Thursday, August 21, 2008)]
[Proposed Rules]
[Pages 49366-49368]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-19363]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0898; Directorate Identifier 2007-NM-200-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767-200 and 767-300 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 767-200 and 767-300 series airplanes. This
proposed AD would require detailed inspections of the aft pressure
bulkhead for damage, mid-frequency eddy current (MFEC) and low
frequency eddy current (LFEC) inspections of radial web lap splices,
tear strap splices, and super tear strap splices for cracking, and
corrective actions if necessary. This AD results from analysis that
indicates fatigue cracks of the web lap splice, tear strap splice, or
super tear strap splice of the aft bulkhead are expected to occur on
certain Boeing Model 767-200 and 767-300 series airplanes. We are
proposing this AD to detect and correct fatigue cracks of the aft
pressure bulkhead, which could result in rapid decompression of the
passenger compartment and possible damage or interference with airplane
control systems that penetrate the bulkhead, and consequent loss of
controllability of the airplane.
DATES: We must receive comments on this proposed AD by October 6, 2008.
ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
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 (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tamara L. Anderson, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6421; fax (425) 917-6590.
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-2008-0898;
Directorate Identifier 2007-NM-200-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
[[Page 49367]]
substantive verbal contact we receive about this proposed AD.
Discussion
We have previously issued AD 2005-03-11, amendment 39-13967 (70 FR
7174, February 11, 2005). (A correction of the rule was published in
the Federal Register on March 11, 2005 (70 FR 12119, March 11, 2005).)
That AD applies to certain Boeing Model 767-200 and 767-300 series
airplanes, line numbers 1 through 175 inclusive. That AD was prompted
by a report of multiple-site fatigue cracking (multiple-site damage) in
two lap splices on the aft pressure bulkhead of one airplane. That AD
currently requires repetitive detailed and eddy current inspections of
the aft pressure bulkhead for damage and cracking, one-time detailed
and high frequency eddy current inspections of any ``oil can'' located
on the aft pressure bulkhead for damage and cracking, and related
corrective actions if necessary.
Since the issuance of that AD, analysis indicates that fatigue
cracks of the web lap splice, tear strap splice, or super tear strap
splice of the aft bulkhead are expected to occur on Boeing Model 767-
200 and 767-300 series airplanes having line numbers 176 through 423
inclusive that have accumulated 35,000 or more total flight cycles.
There have been no reports of such fatigue cracks on these in-service
airplanes. Such fatigue cracking, if not corrected, could result in
rapid decompression of the passenger compartment and possible damage or
interference with airplane control systems that penetrate the bulkhead,
and consequent loss of controllability of the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 767-53A0147, dated
August 16, 2007. The service bulletin describes procedures for:
Doing an initial detailed inspection of the aft pressure
bulkhead for damage such as dents, punctures, nicks, gouges, cracks,
corrosion, and scratches, and repeating those inspections.
Doing initial mid-frequency eddy current (MFEC) and low-
frequency eddy current (LFEC) inspections of the radial web lap
splices, tear strap splices, and super tear strap splices for cracking,
and repeating those inspections.
Contacting Boeing for inspection instructions where
inspection is prevented by a repair common to the inspection area.
Doing applicable corrective actions, which include
repairing any damage that exceeds certain allowable limits, and
contacting Boeing for repair instructions. The service bulletin
specifies the following compliance times:
For the initial inspections: 35,000 total flight-cycles,
or 18 months or 3,000 flight-cycles after the date of the service
bulletin, whichever occurs first.
For the repetitive inspections: Within 3,000 flight-cycles
of the initial inspection, and thereafter at intervals not to exceed
3,000 flight-cycles.
For the applicable corrective actions: Before further
flight.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. For this reason, we are proposing this AD,
which would require accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between Proposed Rule and Service Bulletin.''
Differences Between Proposed Rule and Service Bulletin
The service bulletin specifies to contact the manufacturer for
instructions on how to repair and inspect certain conditions, but this
proposed AD would require repairing and inspecting those conditions in
one of the following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Clarification of Repetitive Inspections Specified in Service Bulletin
The Accomplishment Instructions of the service bulletin specifies
to only repeat the inspections if no crack is found. However, Table 2
of paragraph 1.E, ``Compliance,'' of the service bulletin identifies
repeat intervals for the inspections, regardless of inspection
findings. The intent is that the inspections be repeated for all
findings. Therefore, this proposed AD would require repetitive
inspections at the applicable repeat intervals listed in Table 2 of
paragraph 1.E., ``Compliance.''
Costs of Compliance
There are about 244 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 84 airplanes of
U.S. registry. The proposed actions would take about 31 work hours per
airplane, at an average labor rate of $80 per work hour. Based on these
figures, the estimated cost of the proposed AD for U.S. operators is
$208,320, or $2,480 per airplane, per inspection cycle.
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); and
3. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
[[Page 49368]]
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
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]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2008-0898; Directorate Identifier 2007-NM-
200-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by October
6, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 767-200 and 767-300 series
airplanes, certificated in any category; as identified in Boeing
Alert Service Bulletin 767-53A0147, dated August 16, 2007.
Unsafe Condition
(d) This AD results from analysis that indicates fatigue cracks
of the web lap splice, tear strap splice, or super tear strap splice
of the aft bulkhead are expected to occur on certain Boeing Model
767-200 and 767-300 series airplanes. We are proposing this AD to
detect and correct fatigue cracks of the aft pressure bulkhead,
which could result in rapid decompression of the passenger
compartment and possible damage or interference with airplane
control systems that penetrate the bulkhead, and consequent loss of
controllability of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Inspections and Applicable Related Investigative and Corrective Actions
(f) Except as provided by paragraphs (f)(1) and (f)(2) of this
AD: At the applicable compliance time and repeat intervals listed in
Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 767-53A0147, dated August 16, 2007, do detailed
inspections of the aft pressure bulkhead for damage, mid-frequency
eddy current (MFEC) and low-frequency eddy current (LFEC)
inspections of radial web lap splices, tear strap splices, and super
tear strap splices for cracking and applicable corrective actions by
accomplishing all the applicable actions specified in the
Accomplishment Instructions of the service bulletin.
(1) Where Table 1 of paragraph 1.E., ``Compliance,'' of the
service bulletin specifies a compliance time after the date on the
service bulletin, this AD requires compliance within the specified
compliance time after the effective date of this AD.
(2) Where the service bulletin specifies a compliance time of
``As given by Boeing'' or to contact Boeing for the appropriate
action, this AD requires, before further flight, inspections of the
area of repair and repair of any damaged/cracked part, as
applicable, using a method approved in accordance with the
procedures specified in paragraph (g) of this AD.
Alternative Methods of Compliance (AMOCs)
(g)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Tamara L. Anderson, Aerospace Engineer, Airframe Branch,
ANM-120S, 1601 Lind Avenue, SW., Renton, Washington, telephone (425)
917-6421; fax (425) 917-6590; has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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 an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who 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.
Issued in Renton, Washington, on August 8, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-19363 Filed 8-20-08; 8:45 am]
BILLING CODE 4910-13-P
