Airworthiness Directives; Boeing Model 757-200, -200PF, and -200CB Series Airplanes, 34313-34316 [05-11515]
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Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 / Rules and Regulations
operators to be $2,180, assuming that
one vespel spline adapter that is not
covered by manufacturer’s warranty is
replaced on each helicopter.
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
written data, views, or arguments
regarding this AD. Send your comments
to an address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2005–21373;
Directorate Identifier 2005–SW–13–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the AD. We will consider all comments
received by the closing date and may
amend the 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 AD. Using the
search function of our docket Web site,
you can find and read the comments to
any of our dockets, including the name
of the individual who sent the
comment. 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.
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 the 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 an economic evaluation
of the estimated costs to comply with
this AD. See the DMS to examine the
economic evaluation.
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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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
I
34313
adapter in accordance with paragraph 3.A.,
steps (1) through (6) of the Accomplishment
Instructions in Sikorsky Aircraft Corporation
Alert Service Bulletin No. 92–63–001, dated
April 1, 2005.
(b) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Boston Aircraft
Certification Office, Engine and Propeller
Directorate, FAA, for information about
previously approved alternative methods of
compliance.
(c) The removals and replacements shall be
done in accordance with paragraph 3.A.,
steps (1) through (6) of the Accomplishment
Instructions in Sikorsky Aircraft Alert
Service Bulletin No. 92–63–001, dated April
1, 2005. The Director of the Federal Register
approved this incorporation by reference in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from
Sikorsky Aircraft Corporation, Attn: Manager,
Commercial Tech Support, 6900 Main Street,
Stratford, Connecticut 06614, phone (203)
386–3001, fax (203) 386–5983. Copies may be
inspected at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
(d) This amendment becomes effective on
June 29, 2005.
Issued in Fort Worth, Texas, on June 1,
2005.
Carl F. Mittag,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 05–11516 Filed 6–13–05; 8:45 am]
PART 39—AIRWORTHINESS
DIRECTIVES
BILLING CODE 4910–13–P
1. The authority citation for part 39
continues to read as follows:
DEPARTMENT OF TRANSPORTATION
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
I
2005–12–03 Sikorsky Aircraft Corporation:
Amendment 39–14119. Docket No.
FAA–2005–21373; Directorate Identifier
2005–SW–13–AD.
Applicability: Model S–92A helicopters
with main gearbox (MGB) lubrication/
scavenge pump, part number (P/N) 92351–
15800–101, with vespel spline adapter, P/N
1584000–1, installed, certificated in any
category.
Compliance: Required before further flight,
unless accomplished previously, and
thereafter, at intervals not to exceed 50 hours
time-in-service.
To prevent loss of lubrication to the MGB,
which could cause failure of one or both
engine input drives, or planetary gear to sun
gear tooth mesh failure, resulting in loss of
power to the rotor system and subsequent
loss of control of the helicopter, accomplish
the following:
(a) Remove and replace each MGB
lubrication/scavenge pump vespel spline
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Federal Aviation Administration
[Amended]
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14 CFR Part 39
[Docket No. FAA–2005–21358; Directorate
Identifier 2005–NM–088–AD; Amendment
39–14120; AD 2005–12–04]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757–200, –200PF, and –200CB
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 757–200, –200PF, and
–200CB series airplanes. This AD
requires repetitive inspections of the
shim installation between the vertical
flange and bulkhead. This AD is
prompted by reports of cracks, loose and
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Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 / Rules and Regulations
broken bolts, and shim migration in the
joint between the aft torque bulkhead
and the strut-to-diagonal brace fitting.
We are issuing this AD to detect and
correct such cracks, loose and broken
bolts, and shim migration, which could
result in damage to the strut and
consequent separation of the strut and
engine from the airplane.
DATES: Effective June 29, 2005.
The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of June 29, 2005.
We must receive comments on this
AD by August 15, 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.
For service information identified in
this 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–
21358; the directorate identifier for this
docket is 2005–NM–088–AD.
Examining the Dockets
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
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 (DMS) receives
them.
FOR FURTHER INFORMATION CONTACT:
Dennis Stremick, Aerospace Engineer,
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19:17 Jun 13, 2005
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Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6450; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: Boeing
advises that, since 1993, it has received
17 reports of cracks, loose and broken
bolts, and shim migration in the joint
between the aft torque bulkhead and the
strut-to-diagonal brace fitting on Boeing
Model 757–200 series airplanes. Those
conditions, if not corrected, could result
in damage and consequent loss of the
strut and engine from the airplane.
Other Relevant Rulemaking
On May 25, 2004, we issued AD
2004–12–07, amendment 13666 (69 FR
33561, June 16, 2004). That AD applies
to Boeing Model 757 series airplanes,
line numbers 1 through 735 inclusive,
equipped with Rolls Royce RB211
engines.
That AD requires modification of the
nacelle strut and wing structure; and
inspections for loose/missing fasteners
of certain aft bulkhead fasteners, proper
alignment of the middle gusset of the
inboard side load fitting, cracking of
certain fastener holes; and corrective
action if necessary. That AD cites
various revision levels of Boeing Service
Bulletin 757–54–0035 as the appropriate
source of service information for the
required actions.
That AD also mandated inspections of
the 20 fasteners that are subject to this
new AD. The threshold for those initial
inspections is 15,000 total flight cycles.
We have received reports of missing or
loose fasteners in the affected joint as
low as approximately 7,500 total flight
cycles. In addition, that AD mandated
inspections of the 20 fasteners of
airplanes modified in accordance with
Boeing Service Bulletin 757–54–0035
(original), but did not mandate
inspections for airplanes modified in
accordance with Revisions 1 or 2 of that
service bulletin or airplanes that had
been modified in production. Loose or
missing fasteners have been found on
airplanes with all versions of the
modification.
The actions required by that AD were
intended to prevent fatigue cracking in
primary strut structure and consequent
reduced structural integrity of the strut,
but based on this service experience, we
have concluded that the inspection
requirements of that AD are not
adequate.
Relevant Service Information
We have reviewed Boeing Service
Bulletin 757–54A0047, Revision 1,
dated March 24, 2005. The service
bulletin describes procedures for
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repetitive detailed inspections of the
shim installation between the vertical
flange and bulkhead. Specifically, the
service bulletin provides procedures to:
• Inspect for damaged sealant around
the shim;
• Inspect for signs of shim movement;
• Measure the horizontal and vertical
movement of the shim from the
installed position to determine the total
cumulative movement of the shims;
• Inspect for signs of movement of the
four fasteners in the vertical flange; and
• Detect signs of damaged paint and/
or sealant or signs of movement of the
16 fasteners that hold the bulkhead
assembly to the horizontal flange of the
strut-to-diagonal brace fitting.
The service bulletin also describes
four different interim repairs, depending
on the amount of shim movement
revealed during the inspections. The
various interim repair actions include
doing an eddy current inspection of the
fastener holes for cracks, for which the
service bulletin recommends contacting
the manufacturer for repair instructions;
replacing the shims with new shims;
oversizing the holes and replacing
discrepant fasteners with oversize
fasteners; and applying sealant/primer
on the shim of the vertical flange.
For airplanes modified in accordance
with Service Bulletin 757–54–0035, the
compliance time for the initial
inspection is 6,000 flight cycles/36
months after the modification, with a
grace period of 3,000 flight cycles/18
months. For unmodified airplanes, the
compliance time is 90 days. The
repetitive intervals range from 6,000 to
9,000 flight cycles/36 to 54 months.
Interim repairs are due before further
flight after a positive finding.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
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. Therefore, we are issuing this
AD to detect and correct cracks, loose
and broken bolts, and shim migration in
the joint between the aft torque
bulkhead and the strut-to-diagonal brace
fitting. These conditions could result in
damage to the strut and consequent
separation of the strut and engine from
the airplane. This AD requires
accomplishing the actions specified in
the service information described
previously, except as discussed below.
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Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 / Rules and Regulations
Differences Between the AD and the
Service Bulletin
The service bulletin specifies
compliance times relative to the issue
date of the service bulletin; this AD
requires corresponding compliance
times relative to the effective date of the
AD.
The service bulletin specifies that you
may contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require you to repair those conditions
using either a method that we approve,
or data that meet the certification basis
of the airplane and have been approved
by an Authorized Representative for the
Boeing Delegation Option Authorization
Organization whom we have authorized
to make those findings.
Clarification of Certain Compliance
Times
For Group 2 airplanes, the service
bulletin specifies an inspection
threshold relative to the date of issuance
of the ‘‘original Airworthiness
Certificate * * *’’ For these same
airplanes, however, this AD requires an
inspection threshold relative to the date
of issuance of the ‘‘original standard
airworthiness certificate * * *’’ We find
that the addition of the term ‘‘standard’’
will establish this date with certainty.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD; therefore, providing notice and
opportunity for public comment before
the AD is issued is impracticable, and
good cause exists to make this AD
effective in less than 30 days.
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 an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–21358; Directorate Identifier
2005–NM–088–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD. We will consider all
comments received by the closing date
and may amend the 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
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Jkt 205001
substantive verbal contact with FAA
personnel concerning this 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.
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 the 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 AD. See the ADDRESSES section for
a location to examine the regulatory
evaluation.
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34315
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PART 39—AIRWORTHINESS
DIRECTIVES
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I 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 FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
2005–12–04 Boeing: Amendment 39–14120.
Docket No. FAA–2005–21358;
Directorate Identifier 2005–NM–088–AD.
Effective Date
(a) This AD becomes effective June 29,
2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to
Boeing Model 757–200, –200PF, and –200CB
series airplanes; certificated in any category;
line numbers 1 through 1048 inclusive;
powered by Rolls Royce engines.
Unsafe Condition
(d) This AD was prompted by reports of
cracks, loose and broken bolts, and shim
migration in the joint between the aft torque
bulkhead and the strut-to-diagonal brace
fitting. The FAA is issuing this AD to detect
and correct such conditions, which could
result in damage to the strut and consequent
separation of the strut and 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.
Service Information
(f) For purposes of this AD, ‘‘the service
bulletin’’ refers to Boeing Service Bulletin
757–54A0047, Revision 1, dated March 24,
2005.
Inspections
(g) Inspect the joint between the aft torque
bulkhead and the strut-to-diagonal brace
fitting, and repair any loose shim or loose,
missing, or damaged fastener, by doing all
actions at the times specified in the
Accomplishment Instructions of the service
bulletin, as applicable, except as required by
paragraphs (i), (j), and (k) of this AD.
(h) An inspection and corrective actions
done before the effective date of this AD in
accordance with paragraph (b) or (c), as
applicable, of AD 2004–12–07, amendment
39–13666, are acceptable for compliance
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Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 / Rules and Regulations
with the initial inspection requirement of
paragraph (g) of this AD.
federal_register/code_of_federal_regulations/
ibr_locations.html.
Exceptions to Service Bulletin Procedures
Issued in Renton, Washington, on May 26,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–11515 Filed 6–13–05; 8:45 am]
(i) Where the service bulletin specifies a
compliance time relative to the issue date of
the service bulletin, this AD requires
compliance within the corresponding
specified time relative to the effective date of
this AD.
(j) For purposes of this AD, for Group 2
airplanes having line numbers 736 through
1048, the initial inspection must be done
within the specified time after the date of
issuance of the original standard
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness. The grace period for these
airplanes is 3,000 flights from the effective
date of this AD.
(k) If any crack is found during any
inspection required by this AD, and the
service bulletin specifies to contact Boeing
for appropriate action: Before further flight,
repair the crack according to a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or according
to data meeting the certification basis of the
airplane approved by an Authorized
Representative for the Boeing 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 approval must
specifically refer to this AD.
Alternative Methods of Compliance
(AMOCs)
(l) The Manager, Seattle ACO, 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
required by this AD, if it is approved by an
Authorized Representative for the Boeing
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.
Material Incorporated by Reference
(m) You must use Boeing Service Bulletin
757–54A0047, Revision 1, dated March 24,
2005, to perform the actions that are required
by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approves the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To
get copies of the service information, contact
Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124–2207. To
view the AD docket, go to the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washington,
DC. To review copies of the service
information, go to 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/
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–18998; Directorate
Identifier 2003–NM–253–AD; Amendment
39–14121; AD 2005–12–05]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–200, 737–300, 737–400,
737–500, 737–600, 737–700, 737–800,
737–900, 757–200, and 757–300 Series
Airplanes; and McDonnell Douglas
Model DC–10–10, DC–10–10F, DC–10–
30, DC–10–30F, DC–10–40, MD–10–
10F, MD–10–30F, MD–11, and MD–11F
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain transport
category airplanes. That AD currently
requires modification of the reinforced
flight deck door. This new AD expands
the applicability of the existing AD and
requires other actions related to the
reinforced flight deck door. These other
actions include modifying the door,
inspecting and modifying wiring in the
area, and revising the maintenance
program to require more frequent testing
of the decompression panels of the
flight deck door. This AD is prompted
by reports of discrepancies with the
reinforced flight deck door. We are
issuing this AD to prevent inadvertent
release of the decompression latch and
consequent opening of the
decompression panel in the flight deck
door, or penetration of the flight deck
door by smoke or shrapnel, any of
which could result in injury to the
airplane flightcrew. This AD also
requires finding and fixing wire chafing,
which could result in arcing, fire, and/
or reduced controllability of the
airplane.
This AD becomes effective July
19, 2005.
DATES:
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The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of July 19, 2005.
On July 25, 2003 (68 FR 41063, July
10, 2003), the Director of the Federal
Register approved the incorporation by
reference of certain other publications
listed in the AD.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207; or
C&D Aerospace, 5701 Bolsa Avenue,
Huntington Beach, California 92647–
2063.
DOCKET: The AD docket contains the
proposed AD, comments, and any final
disposition. 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 level of the Nassif Building at
the U.S. Department of Transportation,
400 Seventh Street, SW., room PL–401,
Washington, DC. This docket number is
FAA–2004–18998; the directorate
identifier for this docket is 2003–NM–
253–AD.
FOR FURTHER INFORMATION CONTACT: Ron
Atmur, Aerospace Engineer, Airframe
Branch, ANM–120L, FAA, Los Angeles
Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood,
California 90712–4137; telephone (562)
627–5224; fax (562) 627–5210.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR
part 39) with an AD to supersede AD
2003–14–04, amendment 39–13223 (68
FR 41063, July 10, 2003). The existing
AD applies to certain Boeing Model
737–200, 737–300, 737–400, 737–500,
737–600, 737–700, 737–800, 737–900,
757–200, and 757–300 series airplanes;
and McDonnell Douglas Model DC–10–
10F, DC–10–30, DC–10–30F, DC–10–40,
MD–10–30F, MD–11, and MD–11F
airplanes. The proposed AD was
published in the Federal Register on
September 3, 2004 (69 FR 53848), to
continue to require modification of the
reinforced flight deck door. The
proposed AD would also expand the
applicability of the existing AD and
require other actions related to the
reinforced flight deck door. These other
actions include modifying the door,
inspecting and modifying wiring in the
area, and revising the maintenance
program to require more frequent testing
of the decompression panels of the
flight deck door.
E:\FR\FM\14JNR1.SGM
14JNR1
]]>Agencies
[Federal Register Volume 70, Number 113 (Tuesday, June 14, 2005)]
[Rules and Regulations]
[Pages 34313-34316]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-11515]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21358; Directorate Identifier 2005-NM-088-AD;
Amendment 39-14120; AD 2005-12-04]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 757-200, -200PF, and -
200CB Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 757-200, -200PF, and -200CB series airplanes. This
AD requires repetitive inspections of the shim installation between the
vertical flange and bulkhead. This AD is prompted by reports of cracks,
loose and
[[Page 34314]]
broken bolts, and shim migration in the joint between the aft torque
bulkhead and the strut-to-diagonal brace fitting. We are issuing this
AD to detect and correct such cracks, loose and broken bolts, and shim
migration, which could result in damage to the strut and consequent
separation of the strut and engine from the airplane.
DATES: Effective June 29, 2005.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of June
29, 2005.
We must receive comments on this AD by August 15, 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.
For service information identified in this 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-2005-21358; the directorate identifier for this docket is
2005-NM-088-AD.
Examining the Dockets
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 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
(DMS) receives them.
FOR FURTHER INFORMATION CONTACT: Dennis Stremick, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6450; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: Boeing advises that, since 1993, it has
received 17 reports of cracks, loose and broken bolts, and shim
migration in the joint between the aft torque bulkhead and the strut-
to-diagonal brace fitting on Boeing Model 757-200 series airplanes.
Those conditions, if not corrected, could result in damage and
consequent loss of the strut and engine from the airplane.
Other Relevant Rulemaking
On May 25, 2004, we issued AD 2004-12-07, amendment 13666 (69 FR
33561, June 16, 2004). That AD applies to Boeing Model 757 series
airplanes, line numbers 1 through 735 inclusive, equipped with Rolls
Royce RB211 engines.
That AD requires modification of the nacelle strut and wing
structure; and inspections for loose/missing fasteners of certain aft
bulkhead fasteners, proper alignment of the middle gusset of the
inboard side load fitting, cracking of certain fastener holes; and
corrective action if necessary. That AD cites various revision levels
of Boeing Service Bulletin 757-54-0035 as the appropriate source of
service information for the required actions.
That AD also mandated inspections of the 20 fasteners that are
subject to this new AD. The threshold for those initial inspections is
15,000 total flight cycles. We have received reports of missing or
loose fasteners in the affected joint as low as approximately 7,500
total flight cycles. In addition, that AD mandated inspections of the
20 fasteners of airplanes modified in accordance with Boeing Service
Bulletin 757-54-0035 (original), but did not mandate inspections for
airplanes modified in accordance with Revisions 1 or 2 of that service
bulletin or airplanes that had been modified in production. Loose or
missing fasteners have been found on airplanes with all versions of the
modification.
The actions required by that AD were intended to prevent fatigue
cracking in primary strut structure and consequent reduced structural
integrity of the strut, but based on this service experience, we have
concluded that the inspection requirements of that AD are not adequate.
Relevant Service Information
We have reviewed Boeing Service Bulletin 757-54A0047, Revision 1,
dated March 24, 2005. The service bulletin describes procedures for
repetitive detailed inspections of the shim installation between the
vertical flange and bulkhead. Specifically, the service bulletin
provides procedures to:
Inspect for damaged sealant around the shim;
Inspect for signs of shim movement;
Measure the horizontal and vertical movement of the shim
from the installed position to determine the total cumulative movement
of the shims;
Inspect for signs of movement of the four fasteners in the
vertical flange; and
Detect signs of damaged paint and/or sealant or signs of
movement of the 16 fasteners that hold the bulkhead assembly to the
horizontal flange of the strut-to-diagonal brace fitting.
The service bulletin also describes four different interim repairs,
depending on the amount of shim movement revealed during the
inspections. The various interim repair actions include doing an eddy
current inspection of the fastener holes for cracks, for which the
service bulletin recommends contacting the manufacturer for repair
instructions; replacing the shims with new shims; oversizing the holes
and replacing discrepant fasteners with oversize fasteners; and
applying sealant/primer on the shim of the vertical flange.
For airplanes modified in accordance with Service Bulletin 757-54-
0035, the compliance time for the initial inspection is 6,000 flight
cycles/36 months after the modification, with a grace period of 3,000
flight cycles/18 months. For unmodified airplanes, the compliance time
is 90 days. The repetitive intervals range from 6,000 to 9,000 flight
cycles/36 to 54 months. Interim repairs are due before further flight
after a positive finding.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
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. Therefore, we are
issuing this AD to detect and correct cracks, loose and broken bolts,
and shim migration in the joint between the aft torque bulkhead and the
strut-to-diagonal brace fitting. These conditions could result in
damage to the strut and consequent separation of the strut and engine
from the airplane. This AD requires accomplishing the actions specified
in the service information described previously, except as discussed
below.
[[Page 34315]]
Differences Between the AD and the Service Bulletin
The service bulletin specifies compliance times relative to the
issue date of the service bulletin; this AD requires corresponding
compliance times relative to the effective date of the AD.
The service bulletin specifies that you may contact the
manufacturer for instructions on how to repair certain conditions, but
this proposed AD would require you to repair those conditions using
either a method that we approve, or data that meet the certification
basis of the airplane and have been approved by an Authorized
Representative for the Boeing Delegation Option Authorization
Organization whom we have authorized to make those findings.
Clarification of Certain Compliance Times
For Group 2 airplanes, the service bulletin specifies an inspection
threshold relative to the date of issuance of the ``original
Airworthiness Certificate * * *'' For these same airplanes, however,
this AD requires an inspection threshold relative to the date of
issuance of the ``original standard airworthiness certificate * * *''
We find that the addition of the term ``standard'' will establish this
date with certainty.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and opportunity for public comment
before the AD is issued is impracticable, and good cause exists to make
this AD effective in less than 30 days.
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 an
address listed under ADDRESSES. Include ``Docket No. FAA-2005-21358;
Directorate Identifier 2005-NM-088-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the 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 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.
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 the 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 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, Incorporation by
reference, Safety.
PART 39--AIRWORTHINESS DIRECTIVES
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-12-04 Boeing: Amendment 39-14120. Docket No. FAA-2005-21358;
Directorate Identifier 2005-NM-088-AD.
Effective Date
(a) This AD becomes effective June 29, 2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to Boeing Model 757-200, -
200PF, and -200CB series airplanes; certificated in any category;
line numbers 1 through 1048 inclusive; powered by Rolls Royce
engines.
Unsafe Condition
(d) This AD was prompted by reports of cracks, loose and broken
bolts, and shim migration in the joint between the aft torque
bulkhead and the strut-to-diagonal brace fitting. The FAA is issuing
this AD to detect and correct such conditions, which could result in
damage to the strut and consequent separation of the strut and
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.
Service Information
(f) For purposes of this AD, ``the service bulletin'' refers to
Boeing Service Bulletin 757-54A0047, Revision 1, dated March 24,
2005.
Inspections
(g) Inspect the joint between the aft torque bulkhead and the
strut-to-diagonal brace fitting, and repair any loose shim or loose,
missing, or damaged fastener, by doing all actions at the times
specified in the Accomplishment Instructions of the service
bulletin, as applicable, except as required by paragraphs (i), (j),
and (k) of this AD.
(h) An inspection and corrective actions done before the
effective date of this AD in accordance with paragraph (b) or (c),
as applicable, of AD 2004-12-07, amendment 39-13666, are acceptable
for compliance
[[Page 34316]]
with the initial inspection requirement of paragraph (g) of this AD.
Exceptions to Service Bulletin Procedures
(i) Where the service bulletin specifies a compliance time
relative to the issue date of the service bulletin, this AD requires
compliance within the corresponding specified time relative to the
effective date of this AD.
(j) For purposes of this AD, for Group 2 airplanes having line
numbers 736 through 1048, the initial inspection must be done within
the specified time after the date of issuance of the original
standard airworthiness certificate or the date of issuance of the
original export certificate of airworthiness. The grace period for
these airplanes is 3,000 flights from the effective date of this AD.
(k) If any crack is found during any inspection required by this
AD, and the service bulletin specifies to contact Boeing for
appropriate action: Before further flight, repair the crack
according to a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or according to data meeting the
certification basis of the airplane approved by an Authorized
Representative for the Boeing 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
approval must specifically refer to this AD.
Alternative Methods of Compliance (AMOCs)
(l) The Manager, Seattle ACO, 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 required by this AD, if it is approved by an
Authorized Representative for the Boeing 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.
Material Incorporated by Reference
(m) You must use Boeing Service Bulletin 757-54A0047, Revision
1, dated March 24, 2005, to perform the actions that are required by
this AD, unless the AD specifies otherwise. The Director of the
Federal Register approves the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To
get copies of the service information, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To view
the AD docket, go to the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC. To review copies of the service
information, go to 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 May 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-11515 Filed 6-13-05; 8:45 am]
BILLING CODE 4910-13-P
