Airworthiness Directives; Boeing Model 707 Airplanes and Model 720 and 720B Series Airplanes, 2060-2062 [05-537]
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Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules
in the AFM. Remove any existing copy of AD
2001–10–01 from the AFM.
DEPARTMENT OF TRANSPORTATION
Terminating Action for This AD
(h) Within 8,000 flight hours after the
effective date of this AD, measure the gap
between the APU and the APU exhaust
silencer, install a flush type APU air inlet,
remove any placard on or near the APU start/
stop switch panel that limits APU starts, and
reidentify the APU cowling, in accordance
with EMBRAER Service Bulletin 145–49–
0018, Change 03, dated January 3, 2002,
except as provided by paragraph (j) of this
AD. Doing the actions in paragraph (h) of this
AD terminates the requirements of
paragraphs (f) and (g) of this AD and any
copy of AD 2001–10–01 or this AD may be
removed from the AFM.
Federal Aviation Administration
Prior to or Concurrent Requirements
(i) Prior to or concurrently with the actions
specified in paragraphs (g) and (h) of this AD,
install an APU silencer in accordance with
EMBRAER Service Bulletin 145–49–0009,
Change 07, dated September 1, 2002.
Contact the FAA or Departmento de Aviacao
Civil (DAC)
(j) If, during the actions required by
paragraphs (g) and (h) of this AD, any
measurement exceeds the limits specified in
EMBRAER Service Bulletin 145–49–0017,
Change 01, dated June 7, 2001; or EMBRAER
Service Bulletin 145–49–0018, Change 03,
dated January 3, 2002; as applicable; and the
service bulletin specifies to contact
EMBRAER: Before further flight, repair per a
method approved by either the Manager,
International Branch, ANM–116, FAA,
Transport Airplane Directorate; or the DAC
(or its delegated agent).
Actions Accomplished According to
Previous Issue of Service Bulletin
(k) Actions accomplished before the
effective date of this AD according to
EMBRAER Service Bulletin 145–49–0017,
dated May 15, 2001, are considered
acceptable for compliance with the
corresponding actions specified in this AD.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) AMOCs approved previously in
accordance with AD 2001–10–01,
amendment 39–12226, are approved as
AMOCs for the corresponding requirements
in paragraph (f) of this AD.
Related Information
(m) Brazilian airworthiness directive 2001–
04–02R2, dated June 29, 2001, also addresses
the subject of this AD.
Issued in Renton, Washington, on
December 30, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–539 Filed 1–11–05; 8:45 am]
BILLING CODE 4910–13–U
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14 CFR Part 39
[Docket No. FAA–2005–20023; Directorate
Identifier 2004–NM–49–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 707 Airplanes and Model 720
and 720B Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Boeing Model 707 airplanes and Model
720 and 720B series airplanes. The
existing AD currently requires a
preventive modification of the front spar
fitting on the outboard engine nacelle.
This proposed AD would remove the
requirement to do this preventive
modification, and would require
repetitive inspections for cracking of the
front spar fitting of the inboard and
outboard nacelle struts, and
replacement of any cracked fitting with
a new fitting. The proposed AD would
also apply to more airplanes. This
proposed AD is prompted by a report
indicating that a crack was found in a
front spar fitting that had been replaced
as part of the modification required by
the existing AD. We are proposing this
AD to detect and correct this cracking,
which could result in reduced structural
integrity of the engine nacelle, and
consequent separation of an engine from
the airplane.
DATES: We must receive comments on
this proposed AD by February 28, 2005.
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.
• 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.
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Fmt 4702
Sfmt 4702
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
You can examine the contents of this
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., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20023; the directorate identifier for this
docket is 2004–NM–49–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:
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 under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20023; Directorate Identifier
2004–NM–49–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 our docket
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 can
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can 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
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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 DMS
receives them.
Discussion
On August 20, 2001, we issued AD
2001–17–24, amendment 39–12415 (66
FR 45572, August 29, 2001), for certain
Boeing Model 707 airplanes and 720
and 720B series airplanes. That AD
requires a preventive modification of
the front spar fitting on the outboard
engine nacelle. That AD was prompted
by reports indicating that fatigue cracks
have been found in the front spar fitting
on the outboard engine nacelle. We
issued that AD to prevent this fatigue
cracking, which could reduce the
structural integrity of the nacelle and
result in separation of the engine from
the airplane.
required by AD 2001–17–24. This report
led to a determination that the currently
required modification is not effective in
preventing the previously identified
unsafe condition.
Since we issued AD 2001–17–24, we
have also determined that the front spar
fitting on the inboard engine nacelle
may also be subject to the same unsafe
condition found on the outboard engine
nacelle.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin A3514, dated July 29,
2004. The service bulletin describes
procedures for performing repetitive
detailed inspections for cracking of the
upper surface of the front spar fitting of
nacelle struts 1, 2, 3, and 4; and
replacing any cracked fitting with a new
fitting.
type design. This proposed AD would
supersede AD 2001–17–24. This
proposed AD would remove the
requirement to do the preventive
modification of the front spar fitting on
the outboard engine nacelle. This
proposed AD would require repetitive
inspections for cracking of the front spar
fitting of the inboard and outboard
nacelle struts, and replacement of any
cracked fitting with a new fitting. The
proposed AD would also apply to more
airplanes because it would apply to
airplanes having front spar fittings
previously modified during production.
Explanation of Change to Applicability
We have revised the applicability of
the existing AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
Actions Since Existing AD Was Issued
FAA’s Determination and Requirements
of the Proposed AD
Since we issued AD 2001–17–24, we
have received a report indicating that a
crack was found in a front spar fitting
that had been previously modified as
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
Costs of Compliance
There are about 290 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Work
hours
Action
Inspection (new proposed action) ....................................
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
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Average
labor rate
per hour
8
$65
Cost per
airplane
Parts
None
$520, per inspection
cycle
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. 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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Number
of U.S.registered
airplanes
87
Fleet cost
$45,240
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]
2. The FAA amends § 39.13 by
removing amendment 39–12415 (66 FR
45572, August 29, 2001) and adding the
following new airworthiness directive
(AD):
Boeing: Docket No. FAA–2005–20023;
Directorate Identifier 2004–NM–49–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this airworthiness
directive (AD) action by February 28, 2005.
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Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules
Affected ADs
(b) This AD supersedes AD 2001–17–24,
amendment 39–12415 (66 FR 45572, August
29, 2001).
Applicability
(c) This AD applies to Boeing Model 707–
100 long body, –200, –100B long body, and
–100B short body series airplanes; Model
707–300, –300B, –300C, and –400 series
airplanes; and Model 720 and 720B series
airplanes; certificated in any category; having
line numbers 1 through 1012 inclusive.
Unsafe Condition
(d) This AD was prompted by a report
indicating that a crack was found in a front
spar fitting that had been replaced as part of
the modification required by AD 2001–17–
24, amendment 39–12415. We are issuing
this AD to detect and correct this cracking,
which could result in reduced structural
integrity of the engine nacelle, and
consequent separation of an engine from the
airplane.
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.
Inspection
(f) Prior to the accumulation of 3,500 total
flight hours, or within 18 months after the
effective date of this AD, whichever occurs
later: Do a detailed inspection for cracking of
the front spar fitting of the inboard and
outboard nacelles according to the
Accomplishment Instructions of Boeing Alert
Service Bulletin A3514, dated July 29, 2004.
Repeat the inspection thereafter at intervals
not to exceed 700 flight hours.
Note 1: There is no terminating action at
this time for the repetitive inspections
required by paragraph (f) of this AD.
Replacement
(g) If any cracking is found during any
inspection required by paragraph (f) of this
AD: Before further flight, replace the cracked
front spar fitting with a new fitting, according
to the Accomplishment Instructions of
Boeing Alert Service Bulletin A3514, dated
July 29, 2004.
Parts Installation
(h)(1) As of October 3, 2001 (the effective
date of AD 2001–17–24, amendment 39–
12415), no person may install a front spar
fitting, part number 65–2532 or 65–2532–5,
on the outboard engine nacelle on any
airplane.
(2) As of the effective date of this AD, no
person may install, on any airplane, a front
spar fitting having a part number other than
the part numbers specified in paragraph
2.C.2. of Boeing Alert Service Bulletin
A3514, dated July 29, 2004.
Alternative Methods of Compliance
(AMOCs)
(i)(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.
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(2) An AMOC that provides an acceptable
level of safety may be used for any repair that
is required by this AD, if it is approved by
a Boeing Company Designated Engineering
Representative who has been authorized by
the Manager, Seattle ACO, to make those
findings. For a repair method to be approved,
the approval must specifically refer to this
AD.
Issued in Renton, Washington, on
December 30, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–537 Filed 1–11–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20034; Directorate
Identifier 2004–NM–178–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model DC–10–10, DC–10–10F,
DC–10–15, DC–10–30, DC–10–30F (KC–
10A and KDC–10), DC–10–40, DC–10–
40F, MD–10–10F, MD–10–30F, MD–11,
and MD–11F Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain McDonnell Douglas transport
category airplanes. This proposed AD
would require doing repetitive detailed
inspections for accumulation of debris
(blockage) of the drain holes of the pitot
tubes, and cleaning if any evidence of
debris is found. This proposed AD is
prompted by reports of blocked drain
holes of the pitot tubes. We are
proposing this AD to prevent blocked
drain holes of the pitot tubes, which
could result in the accumulation of
water in the pitot-static system and
consequent failure of that system.
Failure of the pitot-static system could
result in erroneous airspeed indications
in the cockpit and consequent loss of
airspeed control.
DATES: We must receive comments on
this proposed AD by February 28, 2005.
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.
PO 00000
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Fmt 4702
Sfmt 4702
• 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.
• By 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.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Long Beach
Division, 3855 Lakewood Boulevard,
Long Beach, California 90846,
Attention: Data and Service
Management, Dept. C1–L5A (D800–
0024).
You can examine the contents of this
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., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20034; the directorate identifier for this
docket is 2004–NM–178–AD.
FOR FURTHER INFORMATION CONTACT:
Technical information: Brett
Portwood, Aerospace Engineer, Systems
and Equipment Branch, ANM–130L,
FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard,
Lakewood, California 90712–4137;
telephone (562) 627–5350; fax (562)
627–5210.
Plain language information: Marcia
Walters, marcia.walters@faa.gov.
SUPPLEMENTARY INFORMATION:
Docket Management System (DMS)
The FAA has implemented new
procedures for maintaining AD dockets
electronically. As of May 17, 2004, new
AD actions are posted on DMS and
assigned a docket number. We track
each action and assign a corresponding
directorate identifier. The DMS AD
docket number is in the form ‘‘Docket
No. FAA–2005–99999.’’ The Transport
Airplane Directorate identifier is in the
form ‘‘Directorate Identifier 2005–NM–
999–AD.’’ Each DMS AD docket also
lists the directorate identifier (‘‘Old
Docket Number’’) as a cross-reference
for searching purposes.
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 under
ADDRESSES. Include ‘‘Docket No. FAA–
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]]>Agencies
[Federal Register Volume 70, Number 8 (Wednesday, January 12, 2005)]
[Proposed Rules]
[Pages 2060-2062]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-537]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20023; Directorate Identifier 2004-NM-49-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 707 Airplanes and Model
720 and 720B Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Boeing Model 707 airplanes and
Model 720 and 720B series airplanes. The existing AD currently requires
a preventive modification of the front spar fitting on the outboard
engine nacelle. This proposed AD would remove the requirement to do
this preventive modification, and would require repetitive inspections
for cracking of the front spar fitting of the inboard and outboard
nacelle struts, and replacement of any cracked fitting with a new
fitting. The proposed AD would also apply to more airplanes. This
proposed AD is prompted by a report indicating that a crack was found
in a front spar fitting that had been replaced as part of the
modification required by the existing AD. We are proposing this AD to
detect and correct this cracking, which could result in reduced
structural integrity of the engine nacelle, and consequent separation
of an engine from the airplane.
DATES: We must receive comments on this proposed AD by February 28,
2005.
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.
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.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
You can examine the contents of this 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., room PL-
401, on the plaza level of the Nassif Building, Washington, DC. This
docket number is FAA-2005-20023; the directorate identifier for this
docket is 2004-NM-49-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:
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 under ADDRESSES. Include ``Docket No. FAA-2005-20023;
Directorate Identifier 2004-NM-49-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 our
docket 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 can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.
Examining the Docket
You can 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
[[Page 2061]]
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 DMS receives them.
Discussion
On August 20, 2001, we issued AD 2001-17-24, amendment 39-12415 (66
FR 45572, August 29, 2001), for certain Boeing Model 707 airplanes and
720 and 720B series airplanes. That AD requires a preventive
modification of the front spar fitting on the outboard engine nacelle.
That AD was prompted by reports indicating that fatigue cracks have
been found in the front spar fitting on the outboard engine nacelle. We
issued that AD to prevent this fatigue cracking, which could reduce the
structural integrity of the nacelle and result in separation of the
engine from the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2001-17-24, we have received a report indicating
that a crack was found in a front spar fitting that had been previously
modified as required by AD 2001-17-24. This report led to a
determination that the currently required modification is not effective
in preventing the previously identified unsafe condition.
Since we issued AD 2001-17-24, we have also determined that the
front spar fitting on the inboard engine nacelle may also be subject to
the same unsafe condition found on the outboard engine nacelle.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin A3514, dated July
29, 2004. The service bulletin describes procedures for performing
repetitive detailed inspections for cracking of the upper surface of
the front spar fitting of nacelle struts 1, 2, 3, and 4; and replacing
any cracked fitting with a new fitting.
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 products
of this same type design. This proposed AD would supersede AD 2001-17-
24. This proposed AD would remove the requirement to do the preventive
modification of the front spar fitting on the outboard engine nacelle.
This proposed AD would require repetitive inspections for cracking of
the front spar fitting of the inboard and outboard nacelle struts, and
replacement of any cracked fitting with a new fitting. The proposed AD
would also apply to more airplanes because it would apply to airplanes
having front spar fittings previously modified during production.
Explanation of Change to Applicability
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Costs of Compliance
There are about 290 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Work Average U.S.- Fleet
Action hours labor rate Parts Cost per airplane registered cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (new proposed action)........ 8 $65 None $520, per inspection cycle 87 $45,240
--------------------------------------------------------------------------------------------------------------------------------------------------------
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. 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 FAA amends Sec. 39.13 by removing amendment 39-12415 (66 FR
45572, August 29, 2001) and adding the following new airworthiness
directive (AD):
Boeing: Docket No. FAA-2005-20023; Directorate Identifier 2004-NM-
49-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this airworthiness directive (AD) action by February 28, 2005.
[[Page 2062]]
Affected ADs
(b) This AD supersedes AD 2001-17-24, amendment 39-12415 (66 FR
45572, August 29, 2001).
Applicability
(c) This AD applies to Boeing Model 707-100 long body, -200, -
100B long body, and -100B short body series airplanes; Model 707-
300, -300B, -300C, and -400 series airplanes; and Model 720 and 720B
series airplanes; certificated in any category; having line numbers
1 through 1012 inclusive.
Unsafe Condition
(d) This AD was prompted by a report indicating that a crack was
found in a front spar fitting that had been replaced as part of the
modification required by AD 2001-17-24, amendment 39-12415. We are
issuing this AD to detect and correct this cracking, which could
result in reduced structural integrity of the engine nacelle, and
consequent separation of an engine from the airplane.
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.
Inspection
(f) Prior to the accumulation of 3,500 total flight hours, or
within 18 months after the effective date of this AD, whichever
occurs later: Do a detailed inspection for cracking of the front
spar fitting of the inboard and outboard nacelles according to the
Accomplishment Instructions of Boeing Alert Service Bulletin A3514,
dated July 29, 2004. Repeat the inspection thereafter at intervals
not to exceed 700 flight hours.
Note 1: There is no terminating action at this time for the
repetitive inspections required by paragraph (f) of this AD.
Replacement
(g) If any cracking is found during any inspection required by
paragraph (f) of this AD: Before further flight, replace the cracked
front spar fitting with a new fitting, according to the
Accomplishment Instructions of Boeing Alert Service Bulletin A3514,
dated July 29, 2004.
Parts Installation
(h)(1) As of October 3, 2001 (the effective date of AD 2001-17-
24, amendment 39-12415), no person may install a front spar fitting,
part number 65-2532 or 65-2532-5, on the outboard engine nacelle on
any airplane.
(2) As of the effective date of this AD, no person may install,
on any airplane, a front spar fitting having a part number other
than the part numbers specified in paragraph 2.C.2. of Boeing Alert
Service Bulletin A3514, dated July 29, 2004.
Alternative Methods of Compliance (AMOCs)
(i)(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) An AMOC that provides an acceptable level of safety may be
used for any repair that is required by this AD, if it is approved
by a Boeing Company Designated Engineering Representative who has
been authorized by the Manager, Seattle ACO, to make those findings.
For a repair method to be approved, the approval must specifically
refer to this AD.
Issued in Renton, Washington, on December 30, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-537 Filed 1-11-05; 8:45 am]
BILLING CODE 4910-13-P
