Airworthiness Directives; Boeing Model 747-200B, 747-200C, 747-200F, 747-300, and 747SR Series Airplanes, 26888-26890 [E6-7016]
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26888
Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Proposed Rules
(1) For Model A300 airplanes: Airbus A300
AOT 57A0241, dated March 6, 2003.
(2) For Model A300–600 series airplanes:
Airbus A300–600 AOT 57A6096, Revision
01, dated April 11, 2005.
(3) For Model A310 airplanes: Airbus A310
AOT 57A2085, Revision 01, dated April 11,
2005.
Note 1: For the purposes of this AD, a
detailed inspection is defined as: ‘‘An
intensive visual examination of a specific
structural area, system, installation, or
assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface
cleaning and elaborate access procedures
may be required.’’
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(b) For Model A300 airplanes, A300–600
series airplanes, and A310 airplanes
equipped with Dowty Rotol RATs, except
airplanes on which Airbus Modification
12986 has been done: Within 12 months after
the effective date of this AD, replace the RAT
swivel coupling fork fitting with a new steel
fitting, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–0244, dated March
4, 2005 (for Model A300 series airplanes);
A300–57–6099, dated February 23, 2005 (for
Model A300–600 airplanes); or A310–57–
2086, dated March 1, 2005 (for Model A310
airplanes); as applicable.
Revisions
(c) Within 3 months after the effective date
of this AD: Incorporate the information in the
applicable airplane maintenance manual
(AMM) specified in paragraphs (c)(1) and
(c)(2) of this AD, and the Airbus temporary
revision (TR) specified in paragraph (c)(3) of
this AD, into the FAA-approved maintenance
program to specify an inspection for breaks
of the bottom flange of the RAT swivel
coupling yoke fitting after each RAT
extension; and replacement of the RAT
swivel coupling yoke fitting with a new
aluminum part as applicable; in accordance
with method approved by either the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
´ ´
Direction Generale de l’Aviation Civile (or its
delegated agent). The page blocks specified
in paragraphs (c)(1) and (c)(2) of this AD, as
applicable, are one approved method for the
actions required by paragraph (c) of this AD.
Thereafter, except as provided by paragraph
(e) of this AD, no alternative inspection
intervals may be approved for the bottom
flange of the RAT swivel coupling yoke
fitting.
(1) Airbus A300–600 AMM, Chapter 29–
25–00, Page Block 301, dated June 1, 2005.
(2) Airbus A310 AMM, Chapter 29–25–00,
Page Block 301, dated June 1, 2005.
(3) Airbus TR 29–015, dated April 12,
2005, to the Airworthiness Limitations
(AWL) section of the Airbus A300 AMM,
Chapter 29–25–00.
Note 2: After revising the maintenance
program to include the required periodic
inspections according to this paragraph,
operators do not need to make a maintenance
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15:37 May 08, 2006
Jkt 208001
log entry to show compliance with this AD
every time those inspections are
accomplished thereafter.
Note 3: The actions required by paragraph
(c)(3) of this AD may be done by inserting a
copy of TR 29–015 into the AWL section of
the Airbus A300 AMM, Chapter 29–25–00.
When this TR has been included in general
revisions of the AMM, the general revisions
may be inserted in the AMM, provided the
relevant information in the general revision
is identical to that in TR 29–015.
Note 4: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance according
to paragraph (e) of this AD. The request
should include a description of changes to
the required inspections that will ensure the
continued damage tolerance of the affected
structure. The FAA has provided guidance
for this determination in Advisory Circular
(AC) 25–1529.
Credit for Actions Accomplished Previously
(d) Actions done before the effective date
of this AD in accordance with Airbus AOT
57A6096, dated March 6, 2003; or Airbus
AOT 57A2085, dated March 6, 2003; are
acceptable for compliance with the
corresponding action in paragraph (a) of this
AD.
Alternative Methods of Compliance
(e)(1) In accordance with 14 CFR 39.19, the
Manager, International Branch, ANM–116,
FAA, Transport Airplane Directorate, is
authorized to approve alternative methods of
compliance for this AD.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Note 5: The subject of this AD is addressed
in French airworthiness directives F–2005–
089, dated June 8, 2005; F–2005–090 R1,
dated July 6, 2005; and F–2003–149 R1,
dated June 8, 2005.
Issued in Renton, Washington, on April 28,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–7003 Filed 5–8–06; 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–2006–24695; Directorate
Identifier 2006–NM–035–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–200B, 747–200C, 747–200F,
747–300, and 747SR 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 747–200B, 747–
200C, 747–200F, 747–300, and 747SR
series airplanes. This proposed AD
would require doing repetitive
inspections of engine struts 1 through 4,
as applicable, for heat discoloration,
cracking, buckling, or wrinkling. This
proposed AD also would require a
conductivity test to detect the extent of
the heat damage and an inspection to
detect cracking of the heat-discolored,
buckled, or wrinkled area; and repair; if
necessary. This proposed AD results
from reports of heat damage and
cracking of the skin and internal
structure adjacent to and aft of the
precooler exhaust vent on several
engine struts. We are proposing this AD
to detect and correct cracking, buckling,
wrinkling, or heat damage of the skin
and internal structure of the engine
struts, which could result in extensive
damage to the engine struts and
consequent possible separation of an
engine from the airplane during flight.
DATES: We must receive comments on
this proposed AD by June 23, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Governmentwide 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.
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Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Proposed Rules
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6437;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2006–24695; Directorate
Identifier 2006–NM–035–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
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 proposed 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 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 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
We have received reports of heat
damage and cracking of the skin and
internal structure adjacent to and aft of
VerDate Aug<31>2005
15:37 May 08, 2006
Jkt 208001
the precooler exhaust vent on 14 engine
struts on in-service airplanes. These
airplanes had the terminating
modification specified in Boeing Service
Bulletin 747–54–2163 incorporated,
which installed external titanium
doublers and internal frame
reinforcement to originally address
high-temperature air from the precooler
exhaust vent of the engine struts.
However, the reported damage has
occurred in unmodified areas, as well as
modified areas. High-temperature air
from the precooler exhaust vent could
heat up and potentially anneal
(reducing the strength) the skin and
internal structure of the engine struts,
which could result in cracking,
buckling, wrinkling, or heat damage of
the skin and internal structure of the
engine struts. Such cracking, buckling,
wrinkling, or heat damage, if not
detected and corrected, could result in
extensive damage to the engine strut
and consequent possible separation of
an engine from the airplane during
flight.
Other Relevant Rulemaking
We have previously issued AD 95–
13–07, amendment 39–9287 (60 FR
33336, June 28, 1995), applicable to
certain Boeing Model 747 series
airplanes. That AD requires
modifications of the nacelle strut and
wing structure, inspections and checks
to detect discrepancies, and correction
of discrepancies. The actions required
by that AD must be done in accordance
with Boeing Alert Service Bulletin 747–
54A2158, dated November 30, 1994.
That service bulletin refers to several
service bulletins as additional sources of
service information for doing the actions
required by AD 95–13–07. One of those
additional sources is Boeing Service
Bulletin 747–54–2163.
We have determined that the actions
specified in Boeing Service Bulletin
747–54–2163 continue to prevent failure
of the strut and subsequent loss of the
engine. Therefore, this proposed AD
would not affect the requirements of AD
95–13–07.
Relevant Service Information
We have reviewed Boeing Special
Attention Service Bulletin 747–54–
2223, dated January 26, 2006. The
service bulletin describes the following
procedures:
• Doing repetitive detailed
inspections of engine struts 1 through 4,
as applicable, for heat discoloration,
cracking, buckling, or wrinkling;
• Doing a conductivity test to detect
the extent of the heat damage and a
penetrant inspection or high frequency
eddy current (HFEC) inspection to
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26889
detect cracking of the heat-discolored,
buckled, or wrinkled area, if necessary;
• Contacting Boeing for repair
instructions if necessary.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition.
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 the Proposed AD
and Service Bulletin.’’
Differences Between the Proposed AD
and Service Bulletin
The service bulletin specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing 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.
Costs of Compliance
There are about 112 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about 33
airplanes of U.S. registry. The proposed
detailed inspections would take about 4
or 8 work hours per airplane (depending
on the airplane configuration), 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 $10,560 or $21,120, or $320
or $640 per airplane, per inspection
cycle (depending on the airplane
configuration).
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,
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26890
Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Proposed Rules
‘‘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.
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:
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2006–24695;
Directorate Identifier 2006–NM–035–AD.
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15:37 May 08, 2006
Jkt 208001
Comments Due Date
(a) The FAA must receive comments on
this AD action by June 23, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
200B, 747–200C, 747–200F, 747–300, and
747SR series airplanes, certificated in any
category; as identified in Boeing Special
Attention Service Bulletin 747–54–2223,
dated January 26, 2006.
using a method approved in accordance with
the procedures specified in paragraph (j) of
this AD.
(i) If any cracking is found during any
detailed inspection required by paragraph (g)
of this AD, before further flight, repair the
cracking using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD.
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.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle Aircraft
Certification Office (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 § 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, and the
approval must specifically refer to this AD.
Service Bulletin
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–54–2223, dated January
26, 2006.
Issued in Renton, Washington, on April 28,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–7016 Filed 5–8–06; 8:45 am]
Repetitive Detailed Inspections
(g) Within 18 months after the effective
date of this AD, do a detailed inspection of
engine struts 1 through 4, as applicable, for
heat discoloration, cracking, buckling, or
wrinkling, in accordance with the service
bulletin. Repeat the detailed inspection
thereafter at intervals not to exceed 18
months.
BILLING CODE 4910–13–P
Unsafe Condition
(d) This AD results from reports of heat
damage and cracking of the skin and internal
structure adjacent to and aft of the precooler
exhaust vent on several engine struts on inservice airplanes. We are issuing this AD to
detect and correct cracking, buckling,
wrinkling, or heat damage of the skin and
internal structure of the engine struts, which
could result in extensive damage to the
engine struts and consequent possible
separation of an engine from the airplane
during flight.
Corrective Actions
(h) If any heat discoloration, buckling, or
wrinkling is found during any detailed
inspection required by paragraph (g) of this
AD, before further flight, do a conductivity
test to detect the extent of the heat damage
and a penetrant inspection or high frequency
eddy current inspection to detect cracking of
the heat-discolored, buckled, or wrinkled
area, in accordance with the service bulletin.
(1) If the conductivity test results are
within the limits specified in the service
bulletin and no cracking is detected, before
further flight, repair any buckled or wrinkled
area using a method approved in accordance
with the procedures specified in paragraph (j)
of this AD. Heat discoloration does not need
to be repaired if the conductivity test results
of the heat-discolored area are within the
specified limits in the service bulletin.
(2) If the conductivity test results are
outside the limits specified in the service
bulletin or if any cracking is detected, before
further flight, repair any cracking, heat
discoloration, or buckled or wrinkled area
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23673; Directorate
Identifier 2005–NM–233–AD]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135 and
EMB–145, –145ER, –145MR, –145LR,
–145XR, –145MP, and –145EP
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Proposed rule; withdrawal.
AGENCY:
SUMMARY: The FAA withdraws a notice
of proposed rulemaking (NPRM) that
proposed a new airworthiness directive
(AD) for all EMBRAER Model EMB–135
and EMB–145, –145ER, –145MR,
–145LR, –145XR, –145MP, and –145EP
airplanes. The proposed AD would have
required inspecting to determine the
E:\FR\FM\09MYP1.SGM
09MYP1
]]>Agencies
[Federal Register Volume 71, Number 89 (Tuesday, May 9, 2006)]
[Proposed Rules]
[Pages 26888-26890]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-7016]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24695; Directorate Identifier 2006-NM-035-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-200B, 747-200C, 747-
200F, 747-300, and 747SR 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 747-200B, 747-200C, 747-200F, 747-300, and
747SR series airplanes. This proposed AD would require doing repetitive
inspections of engine struts 1 through 4, as applicable, for heat
discoloration, cracking, buckling, or wrinkling. This proposed AD also
would require a conductivity test to detect the extent of the heat
damage and an inspection to detect cracking of the heat-discolored,
buckled, or wrinkled area; and repair; if necessary. This proposed AD
results from reports of heat damage and cracking of the skin and
internal structure adjacent to and aft of the precooler exhaust vent on
several engine struts. We are proposing this AD to detect and correct
cracking, buckling, wrinkling, or heat damage of the skin and internal
structure of the engine struts, which could result in extensive damage
to the engine struts and consequent possible separation of an engine
from the airplane during flight.
DATES: We must receive comments on this proposed AD by June 23, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Governmentwide 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.
[[Page 26889]]
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for the service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
24695; Directorate Identifier 2006-NM-035-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
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 proposed 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 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 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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
We have received reports of heat damage and cracking of the skin
and internal structure adjacent to and aft of the precooler exhaust
vent on 14 engine struts on in-service airplanes. These airplanes had
the terminating modification specified in Boeing Service Bulletin 747-
54-2163 incorporated, which installed external titanium doublers and
internal frame reinforcement to originally address high-temperature air
from the precooler exhaust vent of the engine struts. However, the
reported damage has occurred in unmodified areas, as well as modified
areas. High-temperature air from the precooler exhaust vent could heat
up and potentially anneal (reducing the strength) the skin and internal
structure of the engine struts, which could result in cracking,
buckling, wrinkling, or heat damage of the skin and internal structure
of the engine struts. Such cracking, buckling, wrinkling, or heat
damage, if not detected and corrected, could result in extensive damage
to the engine strut and consequent possible separation of an engine
from the airplane during flight.
Other Relevant Rulemaking
We have previously issued AD 95-13-07, amendment 39-9287 (60 FR
33336, June 28, 1995), applicable to certain Boeing Model 747 series
airplanes. That AD requires modifications of the nacelle strut and wing
structure, inspections and checks to detect discrepancies, and
correction of discrepancies. The actions required by that AD must be
done in accordance with Boeing Alert Service Bulletin 747-54A2158,
dated November 30, 1994. That service bulletin refers to several
service bulletins as additional sources of service information for
doing the actions required by AD 95-13-07. One of those additional
sources is Boeing Service Bulletin 747-54-2163.
We have determined that the actions specified in Boeing Service
Bulletin 747-54-2163 continue to prevent failure of the strut and
subsequent loss of the engine. Therefore, this proposed AD would not
affect the requirements of AD 95-13-07.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 747-54-
2223, dated January 26, 2006. The service bulletin describes the
following procedures:
Doing repetitive detailed inspections of engine struts 1
through 4, as applicable, for heat discoloration, cracking, buckling,
or wrinkling;
Doing a conductivity test to detect the extent of the heat
damage and a penetrant inspection or high frequency eddy current (HFEC)
inspection to detect cracking of the heat-discolored, buckled, or
wrinkled area, if necessary;
Contacting Boeing for repair instructions if necessary.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
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 the Proposed AD and Service Bulletin.''
Differences Between the Proposed AD and Service Bulletin
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing 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.
Costs of Compliance
There are about 112 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 33 airplanes of
U.S. registry. The proposed detailed inspections would take about 4 or
8 work hours per airplane (depending on the airplane configuration), 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 $10,560 or
$21,120, or $320 or $640 per airplane, per inspection cycle (depending
on the airplane configuration).
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,
[[Page 26890]]
``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.
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-2006-24695; Directorate Identifier 2006-NM-
035-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by June 23,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-200B, 747-200C, 747-
200F, 747-300, and 747SR series airplanes, certificated in any
category; as identified in Boeing Special Attention Service Bulletin
747-54-2223, dated January 26, 2006.
Unsafe Condition
(d) This AD results from reports of heat damage and cracking of
the skin and internal structure adjacent to and aft of the precooler
exhaust vent on several engine struts on in-service airplanes. We
are issuing this AD to detect and correct cracking, buckling,
wrinkling, or heat damage of the skin and internal structure of the
engine struts, which could result in extensive damage to the engine
struts and consequent possible separation of an engine from the
airplane during flight.
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.
Service Bulletin
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-54-2223, dated January 26, 2006.
Repetitive Detailed Inspections
(g) Within 18 months after the effective date of this AD, do a
detailed inspection of engine struts 1 through 4, as applicable, for
heat discoloration, cracking, buckling, or wrinkling, in accordance
with the service bulletin. Repeat the detailed inspection thereafter
at intervals not to exceed 18 months.
Corrective Actions
(h) If any heat discoloration, buckling, or wrinkling is found
during any detailed inspection required by paragraph (g) of this AD,
before further flight, do a conductivity test to detect the extent
of the heat damage and a penetrant inspection or high frequency eddy
current inspection to detect cracking of the heat-discolored,
buckled, or wrinkled area, in accordance with the service bulletin.
(1) If the conductivity test results are within the limits
specified in the service bulletin and no cracking is detected,
before further flight, repair any buckled or wrinkled area using a
method approved in accordance with the procedures specified in
paragraph (j) of this AD. Heat discoloration does not need to be
repaired if the conductivity test results of the heat-discolored
area are within the specified limits in the service bulletin.
(2) If the conductivity test results are outside the limits
specified in the service bulletin or if any cracking is detected,
before further flight, repair any cracking, heat discoloration, or
buckled or wrinkled area using a method approved in accordance with
the procedures specified in paragraph (j) of this AD.
(i) If any cracking is found during any detailed inspection
required by paragraph (g) of this AD, before further flight, repair
the cracking using a method approved in accordance with the
procedures specified in paragraph (j) of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Seattle Aircraft Certification Office (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 Sec.
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, and the approval must specifically refer to this
AD.
Issued in Renton, Washington, on April 28, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-7016 Filed 5-8-06; 8:45 am]
BILLING CODE 4910-13-P
