Airworthiness Directives; Boeing Model 767-200, -300, and -300F Series Airplanes, 58000-58002 [05-19939]
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58000
Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding an airworthiness directive
(AD) that removes amendment 39–7031
(56 FR 26610, June 10, 1991), to read as
follows:
I
2005–20–31 Honeywell: Amendment 39–
14328. Docket No. FAA–2005–22585;
Directorate Identifier 2005–NM–041–AD.
Rescinds AD 91–08–51, Amendment 39–
7031.
Effective Date
(a) This AD becomes effective October 5,
2005.
Affected ADs
(b) This action rescinds AD 91–08–51.
Applicability
(c) This action applies to Honeywell Flight
Management System (FMS) one million word
(1M or 700K) data bases (9104 cycle or
earlier), as installed in, but not limited to,
McDonnell Douglas Model MD–11 and MD–
11F airplanes, and Boeing Model 747–400
series airplanes, Model 757–200, –200PF,
–200CB, and –300 series airplanes, and
Model 767–200, –300, –300F, and –400ER
series airplanes, certificated in any category.
Issued in Renton, Washington, on
September 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–19938 Filed 10–4–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22584; Directorate
Identifier 2005–NM–044–AD; Amendment
39–14313; AD 2004–19–06 R1]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767–200, –300, and –300F Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is revising an
existing airworthiness directive (AD)
that applies to all Boeing Model 767–
200, –300, and –300F series airplanes.
VerDate Aug<31>2005
14:00 Oct 04, 2005
Jkt 208001
The existing AD currently requires
inspections to detect cracking or
corrosion of the fail-safe straps between
the side fitting of the rear spar bulkhead
at body station 955 and the skin; and
follow-on/corrective actions. The
existing AD results from reports of
cracked and/or corroded fail-safe straps
at body station (BS) 955 on Boeing
Model 767–200 series airplanes. We
issued the existing AD to detect and
correct fatigue cracking or corrosion of
the fail-safe straps, which could result
in cracking of adjacent structure and
consequent reduced structural integrity
of the fuselage. This new AD revises the
applicability of the existing AD to
reduce the number of affected airplanes.
We are issuing this AD to detect and
correct fatigue cracking or corrosion of
the fail-safe straps, which could result
in cracking of adjacent structure and
consequent reduced structural integrity
of the fuselage.
DATES: The effective date of this AD is
November 1, 2004.
On November 1, 2004 (69 FR 57636,
September 27, 2004), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin 767–53A0100,
dated September 26, 2002.
We must receive comments on this
AD by December 5, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-Wide Rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Candice Gerretsen, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6428; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
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Discussion
On September 13, 2004, we issued AD
2004–19–06, amendment 39–13800 (69
FR 57636, September 27, 2004). That
AD applies to all Boeing Model 767–
200, –300, and –300F series airplanes.
That AD requires inspections to detect
cracking or corrosion of the fail-safe
straps between the side fitting of the
rear spar bulkhead at body station (BS)
955 and the skin; and follow-on/
corrective actions. That AD resulted
from reports of cracked and/or corroded
fail-safe straps at BS 955 on Boeing
Model 767–200 series airplanes. The
actions specified in that AD are
intended to detect and correct fatigue
cracking or corrosion of the fail-safe
straps, which could result in cracking of
adjacent structure and consequent
reduced structural integrity of the
fuselage.
Actions Since AD Was Issued
Since we issued that AD, the
manufacturer, Boeing, developed a
production change that lowers the
maximum stress in the fail-safe strap
and removes the critical location where
cracks were occurring on Boeing Model
767–200, –300, and –300F series
airplanes. The production change is
applicable to airplanes having line
numbers 932 and subsequent. Therefore,
we have revised the applicability of AD
2004–19–06 to Boeing Model 767–200,
–300, and –300F series airplanes, line
numbers 1 through 931 inclusive.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other airplanes of the same type
design that may be registered in the U.S.
at some time in the future. For this
reason, we are issuing this AD to detect
and correct fatigue cracking or corrosion
of the fail-safe straps, which could
result in cracking of adjacent structure
and consequent reduced structural
integrity of the fuselage. This AD
continues to require inspections to
detect cracking or corrosion of the failsafe straps between the side fitting of
the rear spar bulkhead at body station
955 and the skin; and follow-on/
corrective actions. This AD also revises
the applicability of the existing AD to
exclude line numbers 932 and
subsequent.
Explanation of Change Made to This
AD
Boeing Commercial Airplanes has
received a Delegation Option
Authorization (DOA). We have revised
this AD to delegate the authority to
approve an alternative method of
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Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations
compliance for any repair required by
this AD to an Authorized Representative
for the Boeing Commercial Airplanes
DOA rather than a Designated
Engineering Representative (DER).
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this AD to clarify the
appropriate procedure for notifying the
principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Interim Action
This is considered to be interim
action until final action is identified, at
which time we may consider further
rulemaking.
Costs of Compliance
There are approximately 833
airplanes of the affected design in the
worldwide fleet. We estimate that 354
airplanes of U.S. registry will be affected
by this AD, that it will take
approximately 2 work hours per
airplane to accomplish the required
inspections, and that the average labor
rate is $65 per work hour. Based on
these figures, the cost impact of the AD
on U.S. operators is estimated to be
$46,020, or $130 per airplane, per
inspection cycle.
FAA’s Determination of the Effective
Date
On April 18, 2005, the Seattle Aircraft
Certification Office granted an
alternative method of compliance
(AMOC) with the requirements of AD
2004–19–06 for airplanes having line
numbers 932 and subsequent. That
AMOC terminates the requirements of
AD 2004–19–06 for those airplanes.
This AD clarifies that the applicability
of AD 2004–19–06 is only for airplanes
having line numbers 1 through 931
inclusive. Therefore, providing notice
and opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to the address listed under
the ADDRESSES section. Include ‘‘Docket
No. FAA–2005–22584; Directorate
Identifier 2005–NM–044–AD’’ at the
beginning of your comments. We
specifically invite comments on the
VerDate Aug<31>2005
14:00 Oct 04, 2005
Jkt 208001
58001
overall regulatory, economic,
environmental, and energy aspects of
the AD that might suggest a need to
modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); 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 AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9:00 a.m. and
5:00 p.m., Monday through Friday,
except Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
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List of Subjects in 14 CFR Part 39
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13800 (69
FR 57636, September 27, 2004) and
adding the following new airworthiness
directive (AD):
I
2004–19–06 R1 Boeing: Amendment 39–
14313. Docket No. FAA–2005–22584;
Directorate Identifier 2005–NM–044–AD.
Effective Date
(a) The effective date of this AD is
November 1, 2004.
Affected ADs
(b) This AD revises AD 2004–19–06.
Applicability
(c) This AD applies to Boeing Model 767–
200, –300, and –300F series airplanes,
certificated in any category; line numbers 1
through 931 inclusive.
Unsafe Condition
(d) This AD results from reports of cracked
and/or corroded fail-safe straps at body
station (BS) 955 on Boeing Model 767–200
series airplanes. We are issuing this AD to
detect and correct fatigue cracking or
corrosion of the fail-safe straps, which could
E:\FR\FM\05OCR1.SGM
05OCR1
58002
Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations
result in cracking of adjacent structure and
consequent reduced structural integrity of the
fuselage.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Inspections and Follow-On/Corrective
Actions
(f) Except as provided by paragraph (g) of
this AD, prior to the accumulation of 15,000
total flight cycles, or within 3,000 flight
cycles after November 1, 2004 (the effective
date of AD 2004–19–06), whichever occurs
later, perform a detailed inspection and eddy
current inspection to detect cracking or
corrosion of the fail-safe straps between the
side fitting of the rear spar bulkhead at BS
955 and the skin, per Figure 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–53A0100, dated
September 26, 2002.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
(1) If no crack or corrosion is found, repeat
the inspections thereafter at intervals not to
exceed 6,000 flight cycles or 36 months,
whichever occurs first.
(2) If any crack or corrosion is found,
before further flight, repair per a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or using a
method approved in accordance with
paragraph (h)(2) of this AD.
(g) For airplanes on which the fail-safe
strap has been replaced before November 1,
2004: Do the actions required by paragraph
(f) of this AD within 12,000 flight cycles after
accomplishing the replacement.
Note 2: Steps 2 and 8 of the Work
Instructions of Boeing Alert Service Bulletin
767–53A0100, dated September 26, 2002,
refer incorrectly to 767 Airplane
Maintenance Manual (AMM) 32–00–20 for
opening the MLG doors; the correct reference
is 767 AMM 32–00–15, which is referred to
in steps 3 and 7 of the Work Instructions.
Step 2 also should state ‘‘Open Main Landing
Gear (MLG) doors’’ instead of ‘‘Open Main
Landing Green (MLG) doors.’’
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
VerDate Aug<31>2005
14:00 Oct 04, 2005
Jkt 208001
(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.
Material Incorporated by Reference
(i) You must use Boeing Alert Service
Bulletin 767–53A0100, dated September 26,
2002, to perform the actions that are required
by this AD, unless the AD specifies
otherwise. On November 1, 2004 (69 FR
57636, September 27, 2004), the Director of
the Federal Register approved the
incorporation by reference of this document.
Contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207,
for a copy of this service information. You
may review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street SW., room PL–401, Nassif
Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
September 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–19939 Filed 10–4–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21085; Directorate
Identifier 2004–NM–252–AD; Amendment
39–14307; AD 2005–20–13]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 727 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Boeing Model 727 airplanes. This AD
requires a one-time inspection of the
lower lobe frames of body section 43 to
find open holes between stringers 17L
and 17R and to record their location;
repetitive high frequency eddy current
(HFEC) inspections for cracks of all
open holes; and related investigative
and corrective actions if necessary. This
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Fmt 4700
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AD also includes an optional
terminating action of installing rivets in
all open tooling holes and all unused
lining holes, which would terminate the
repetitive open-hole HFEC inspections
once a hole is plugged with a rivet. This
AD results from reports of cracks at
open tooling holes in the lower lobe
frames of body section 43. We are
issuing this AD to detect and correct
cracks in the frames, which could result
in cracks in the skin panels and rapid
decompression of the airplane.
DATES: This AD becomes effective
November 9, 2005.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of November 9, 2005.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Daniel F. Kutz, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6456; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to all Boeing Model 727 airplanes.
That NPRM was published in the
Federal Register on May 2, 2005 (70 FR
22618). That NPRM proposed to require
a one-time inspection of the lower lobe
frames of body section 43 to find open
holes between stringers 17L and 17R
and to record their location; repetitive
high frequency eddy current (HFEC)
inspections for cracks of all open holes;
and related investigative and corrective
actions if necessary. That NPRM also
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05OCR1
]]>Agencies
[Federal Register Volume 70, Number 192 (Wednesday, October 5, 2005)]
[Rules and Regulations]
[Pages 58000-58002]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-19939]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22584; Directorate Identifier 2005-NM-044-AD;
Amendment 39-14313; AD 2004-19-06 R1]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767-200, -300, and -300F
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is revising an existing airworthiness directive (AD)
that applies to all Boeing Model 767-200, -300, and -300F series
airplanes. The existing AD currently requires inspections to detect
cracking or corrosion of the fail-safe straps between the side fitting
of the rear spar bulkhead at body station 955 and the skin; and follow-
on/corrective actions. The existing AD results from reports of cracked
and/or corroded fail-safe straps at body station (BS) 955 on Boeing
Model 767-200 series airplanes. We issued the existing AD to detect and
correct fatigue cracking or corrosion of the fail-safe straps, which
could result in cracking of adjacent structure and consequent reduced
structural integrity of the fuselage. This new AD revises the
applicability of the existing AD to reduce the number of affected
airplanes. We are issuing this AD to detect and correct fatigue
cracking or corrosion of the fail-safe straps, which could result in
cracking of adjacent structure and consequent reduced structural
integrity of the fuselage.
DATES: The effective date of this AD is November 1, 2004.
On November 1, 2004 (69 FR 57636, September 27, 2004), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 767-53A0100, dated September 26, 2002.
We must receive comments on this AD by December 5, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-Wide Rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6428; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
On September 13, 2004, we issued AD 2004-19-06, amendment 39-13800
(69 FR 57636, September 27, 2004). That AD applies to all Boeing Model
767-200, -300, and -300F series airplanes. That AD requires inspections
to detect cracking or corrosion of the fail-safe straps between the
side fitting of the rear spar bulkhead at body station (BS) 955 and the
skin; and follow-on/corrective actions. That AD resulted from reports
of cracked and/or corroded fail-safe straps at BS 955 on Boeing Model
767-200 series airplanes. The actions specified in that AD are intended
to detect and correct fatigue cracking or corrosion of the fail-safe
straps, which could result in cracking of adjacent structure and
consequent reduced structural integrity of the fuselage.
Actions Since AD Was Issued
Since we issued that AD, the manufacturer, Boeing, developed a
production change that lowers the maximum stress in the fail-safe strap
and removes the critical location where cracks were occurring on Boeing
Model 767-200, -300, and -300F series airplanes. The production change
is applicable to airplanes having line numbers 932 and subsequent.
Therefore, we have revised the applicability of AD 2004-19-06 to Boeing
Model 767-200, -300, and -300F series airplanes, line numbers 1 through
931 inclusive.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design that may be
registered in the U.S. at some time in the future. For this reason, we
are issuing this AD to detect and correct fatigue cracking or corrosion
of the fail-safe straps, which could result in cracking of adjacent
structure and consequent reduced structural integrity of the fuselage.
This AD continues to require inspections to detect cracking or
corrosion of the fail-safe straps between the side fitting of the rear
spar bulkhead at body station 955 and the skin; and follow-on/
corrective actions. This AD also revises the applicability of the
existing AD to exclude line numbers 932 and subsequent.
Explanation of Change Made to This AD
Boeing Commercial Airplanes has received a Delegation Option
Authorization (DOA). We have revised this AD to delegate the authority
to approve an alternative method of
[[Page 58001]]
compliance for any repair required by this AD to an Authorized
Representative for the Boeing Commercial Airplanes DOA rather than a
Designated Engineering Representative (DER).
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this AD to clarify the appropriate procedure for
notifying the principal inspector before using any approved AMOC on any
airplane to which the AMOC applies.
Interim Action
This is considered to be interim action until final action is
identified, at which time we may consider further rulemaking.
Costs of Compliance
There are approximately 833 airplanes of the affected design in the
worldwide fleet. We estimate that 354 airplanes of U.S. registry will
be affected by this AD, that it will take approximately 2 work hours
per airplane to accomplish the required inspections, and that the
average labor rate is $65 per work hour. Based on these figures, the
cost impact of the AD on U.S. operators is estimated to be $46,020, or
$130 per airplane, per inspection cycle.
FAA's Determination of the Effective Date
On April 18, 2005, the Seattle Aircraft Certification Office
granted an alternative method of compliance (AMOC) with the
requirements of AD 2004-19-06 for airplanes having line numbers 932 and
subsequent. That AMOC terminates the requirements of AD 2004-19-06 for
those airplanes. This AD clarifies that the applicability of AD 2004-
19-06 is only for airplanes having line numbers 1 through 931
inclusive. Therefore, providing notice and opportunity for public
comment is unnecessary before this AD is issued, and this AD may be
made effective in less than 30 days after it is published in the
Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to the
address listed under the ADDRESSES section. Include ``Docket No. FAA-
2005-22584; Directorate Identifier 2005-NM-044-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the AD that
might suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9:00 a.m. and 5:00 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); 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 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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-13800 (69 FR 57636, September 27, 2004) and
adding the following new airworthiness directive (AD):
2004-19-06 R1 Boeing: Amendment 39-14313. Docket No. FAA-2005-22584;
Directorate Identifier 2005-NM-044-AD.
Effective Date
(a) The effective date of this AD is November 1, 2004.
Affected ADs
(b) This AD revises AD 2004-19-06.
Applicability
(c) This AD applies to Boeing Model 767-200, -300, and -300F
series airplanes, certificated in any category; line numbers 1
through 931 inclusive.
Unsafe Condition
(d) This AD results from reports of cracked and/or corroded
fail-safe straps at body station (BS) 955 on Boeing Model 767-200
series airplanes. We are issuing this AD to detect and correct
fatigue cracking or corrosion of the fail-safe straps, which could
[[Page 58002]]
result in cracking of adjacent structure and consequent reduced
structural integrity of the fuselage.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspections and Follow-On/Corrective Actions
(f) Except as provided by paragraph (g) of this AD, prior to the
accumulation of 15,000 total flight cycles, or within 3,000 flight
cycles after November 1, 2004 (the effective date of AD 2004-19-06),
whichever occurs later, perform a detailed inspection and eddy
current inspection to detect cracking or corrosion of the fail-safe
straps between the side fitting of the rear spar bulkhead at BS 955
and the skin, per Figure 2 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 767-53A0100, dated September 26, 2002.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(1) If no crack or corrosion is found, repeat the inspections
thereafter at intervals not to exceed 6,000 flight cycles or 36
months, whichever occurs first.
(2) If any crack or corrosion is found, before further flight,
repair per a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or using a method approved in
accordance with paragraph (h)(2) of this AD.
(g) For airplanes on which the fail-safe strap has been replaced
before November 1, 2004: Do the actions required by paragraph (f) of
this AD within 12,000 flight cycles after accomplishing the
replacement.
Note 2: Steps 2 and 8 of the Work Instructions of Boeing Alert
Service Bulletin 767-53A0100, dated September 26, 2002, refer
incorrectly to 767 Airplane Maintenance Manual (AMM) 32-00-20 for
opening the MLG doors; the correct reference is 767 AMM 32-00-15,
which is referred to in steps 3 and 7 of the Work Instructions. Step
2 also should state ``Open Main Landing Gear (MLG) doors'' instead
of ``Open Main Landing Green (MLG) doors.''
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
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 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.
Material Incorporated by Reference
(i) You must use Boeing Alert Service Bulletin 767-53A0100,
dated September 26, 2002, to perform the actions that are required
by this AD, unless the AD specifies otherwise. On November 1, 2004
(69 FR 57636, September 27, 2004), the Director of the Federal
Register approved the incorporation by reference of this document.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_ locations. html.
Issued in Renton, Washington, on September 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-19939 Filed 10-4-05; 8:45 am]
BILLING CODE 4910-13-P
