Airworthiness Directives; Boeing Model 757-200 and -200PF Series Airplanes, 16403-16406 [05-6259]
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Federal Register / Vol. 70, No. 61 / Thursday, March 31, 2005 / Rules and Regulations
the repetitive inspections requirement
specified in paragraph (h) of this AD for that
actuator.
Credit for Actions Previously Completed
(j) Inspections completed before the
effective date of this AD using GE ASB No.
CF34–8C–AL S/B 75–A0007, Revision 1
dated November 7, 2003; or Revision 2 dated
December 16, 2004; or Revision 3 dated
February 14, 2005; are acceptable for
compliance with the corresponding
inspection in this AD.
Alternative Methods of Compliance
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–18876; Directorate
Identifier 2003–NM–254–AD; Amendment
39–14032; AD 2005–07–08]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757–200 and –200PF Series
Airplanes
(k) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
AGENCY:
Special Flight Permits
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 757–200 and –200PF
series airplanes. This AD requires
repetitive inspections and audible tap
tests of the upper and lower skins of the
trailing edge wedges on certain slats,
and related investigative and corrective
actions if necessary. This AD also
provides an optional terminating action
for the repetitive inspections and
audible tap tests. This AD is prompted
by a report of damage to the No. 4
leading edge slat. We are issuing this
AD to prevent delamination of the
leading edge slats, possible loss of
pieces of the trailing edge wedge
assembly during flight, reduction of the
reduced maneuver and stall margins,
and consequent reduced controllability
of the airplane.
DATES: This AD becomes effective May
5, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of May 5, 2005.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207. You
can examine this information 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.
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
(l) Under 39.23, we impose the following
conditions and limitations on the issuance
and use of Special Flight Permits for this AD:
(1) If both engines report FADEC fault 1
messages at the same time, whether
intermittent or continuous, review the MDC
for master VG actuator faults before further
flight. If actuator faults are still present for
both engines, then replace at least one master
VG actuator before further flight.
(2) If a master VG actuator switches
channels, replace the actuator before further
flight.
Material Incorporated by Reference
(m) You must use GE Alert Service Bulletin
No. CF34–8C–AL S/B 75–A0007, Revision 3,
dated February 14, 2005, to perform the
reviews and actuator dispositions required by
this AD. The Director of the Federal Register
approved the incorporation by reference of
GE Alert Service Bulletin No. CF34–8C–AL
S/B 75–A0007, Revision 3, dated February
14, 2005, under 5 U.S.C. 552(a) and 1 CFR
part 51. You can get a copy from General
Electric Company via Lockheed Martin
Technology Services, 10525 Chester Road,
Suite C, Cincinnati, Ohio 45215, telephone
(513) 672–8400, fax (513) 672–8422. You may
review copies at the Federal Aviation
Administration (FAA), New England Region,
Office of the Regional Counsel, 12 New
England Executive Park, Burlington, MA
01803–5299; or 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.
Related Information
(n) None.
Issued in Burlington, Massachusetts, on
March 23, 2005.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–6247 Filed 3–30–05; 8:45 am]
BILLING CODE 4910–13–P
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16:09 Mar 30, 2005
Jkt 205001
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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16403
(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–2004–18876; the directorate
identifier for this docket is 2003–NM–
254–AD.
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) 914–6590.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR Part 39 with
an AD for certain Boeing Model 757–
200 and -200PF series airplanes. That
action, published in the Federal
Register on August 17, 2004 (69 FR
51015), proposed to require repetitive
inspections and audible tap tests of the
upper and lower skins of the trailing
edge wedges on certain slats, and
related investigative and corrective
actions if necessary. The proposed AD
also provided an optional terminating
action for the repetitive inspections and
audible tap tests.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD.
Supportive Comment
One commenter supports the
proposed AD.
Request To Correct Typographical
Error in Applicability
One commenter requests that the
typographical error in paragraph (c),
Applicability, of the proposed AD, be
corrected. The Applicability in the
proposed AD states that the AD applies
to Boeing Model 737–200 and –200F
series airplanes, as listed in Boeing
Alert Service Bulletin 757–57A0063,
dated June 26, 2003. The commenter
states that the reference to Model 737–
200 and –200F series airplanes should
be corrected to avoid confusion between
the referenced service bulletin and
proposed AD.
We agree and the Applicability
section of this AD has been corrected to
reference ‘‘Boeing Model 757–200 and
–200PF series airplanes identified in
Boeing Alert Service Bulletin 757–
57A0063. * * *’’ We discovered this
error after the proposed AD was
published. We find that our intent in the
proposed AD was clear, as all other
references throughout the proposed AD
were correct, and the referenced service
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bulletin applies to Boeing Model 757–
200 and –200PF series airplanes. Thus,
we find no reason to re-open the
comment period.
AD is unclear with respect to these
configurations, and recommends that
we revise the proposed AD to clearly
state the applicability with respect to
the various configurations resulting
from the aforementioned airworthiness
directives and service bulletins.
We do not agree that the applicability
of this AD requires revision. The
applicability of this AD states that the
AD applies to Boeing Model 757–200
and -200PF series airplanes, certificated
in any category, identified in Boeing
Alert Service Bulletin 757–57A0063,
dated June 26, 2003. The effectivity in
that service bulletin is all Boeing Model
757 series airplanes with line numbers
1 through 139 inclusive. This AD
addresses line numbers 1 through 139
inclusive, regardless of configuration.
Also, the airplane applicability for AD
Request To Clarify Applicability
The Air Transport Association (ATA)
states that its member airlines concur
with the intent of the proposed AD, but
that the applicability of the proposed
AD is unclear. The commenter notes
that actions specified in the proposed
AD overlap or duplicate the
requirements of AD 90–23–06,
amendment 39–6794. The commenter
also states that several slat wedge
configurations exist in in-service
airplanes as a result of AD 91–22–51,
amendment 39–8129, and several other
service bulletins that address trailing
edge wedges. The commenter contends
that the applicability of the proposed
91–22–51 has different line numbers
from those in this AD. The applicability
for that AD is Boeing Model 757 series
airplanes, line numbers 140 through
335. We have not changed this AD
regarding this issue.
Request To Give Credit for Actions
Accomplished Previously
One commenter requests that the
proposed AD be revised to indicate that
actions accomplished previously in
accordance with Boeing Service Bulletin
757–57A0038 or 757–57A0045 are
acceptable for compliance with the
requirements of the proposed AD. The
commenter states that the actions
described in those service bulletins have
the same results as the actions described
in Boeing Alert Service Bulletin 757–
57A0063, dated June 26, 2003.
SERVICE BULLETINS WITH SIMILAR ACTIONS
Service Bulletin—
Dated—
Is cited in—
As the appropriate source of
service information for—
Boeing Alert Service Bulletin 757–
57A0063.
Boeing Service Bulletin 757–57A0038,
Revision 2.
Boeing Service Bulletin 757–57A0045 ......
June 26, 2003 ...........................
The proposed AD .....................
October 10, 1990 ......................
AD 90–23–06, amendment 39–
6794.
AD 91–22–51, amendment 39–
8129.
Inspecting, repairing, and replacing trailing edge wedges.
Inspecting, repairing, and replacing trailing edge wedges.
Repetitive detailed inspections
of the trailing edge wedges
of slats 1 through 4 and 7
through 10.
October 16, 1991 ......................
We agree that accomplishment of the
actions specified in Boeing Service
Bulletin 757–57A0038, Revision 5,
dated July 16, 1992, or Revision 6, dated
November 10, 1994, only, are acceptable
for compliance with the requirements of
this AD. We do not agree that
accomplishment of the actions specified
in Boeing Service Bulletin 757–57A0045
is acceptable for compliance with the
requirements of this AD. As stated
previously, the applicability of AD 91–
22–51 is Boeing Model 757 series
airplanes, line numbers 140 through 335
inclusive, and the applicability of this
AD is line numbers 1 through 139
inclusive.
We have included a new paragraph
(h) in this AD, and reidentified the
subsequent paragraphs accordingly.
Paragraph (h) specifies that
accomplishment of the actions in the
Accomplishment Instructions of Boeing
Service Bulletin 757–57A0038, Revision
5 or Revision 6 only, in conjunction
with the use of BMS 5–137 adhesive, is
acceptable for compliance with the
requirements of this AD.
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Request To Revise Compliance Time for
Repetitive Inspections and Tests
One commenter requests an extension
of the compliance time from 18 months
to 24 months for the repetitive detailed
inspections and audible tap tests of the
upper and lower skins of the trailing
edge wedges. The commenter states that
it performs maintenance checks (‘‘Cchecks’’) on its fleet every 24 months.
The commenter also states that a
compliance time of 18 months would
require special maintenance visits in
addition to the normally scheduled ‘‘Cchecks,’’ and the associated costs and
downtime would be considerable. The
commenter has reviewed its
maintenance program, and the subject
slats are currently inspected every 48
months. A review of the associated
maintenance task cards did not reveal
any discrepancies. The commenter
notes that this change to the proposed
AD would prevent operators from
having to request approval of an AMOC
for the proposed AD.
We do not agree with the commenter’s
request to extend the compliance time.
In developing an appropriate
compliance time for this AD, we
considered the urgency associated with
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the subject unsafe condition, the
manufacturer’s recommended
compliance time, and the practical
aspect of accomplishing the required
inspections within a period of time that
corresponds to the normal scheduled
maintenance program for most affected
operators. However, according to the
provisions of paragraph (k) of this AD,
we may approve a request to adjust the
compliance time if the request includes
data that prove that the new compliance
time would provide an acceptable level
of safety.
Explanation of Additional Change to
This AD
Since the publication of the proposed
AD, Boeing has received a Delegation
Option Authorization (DOA). We have
revised this AD to delegate the authority
to approve an AMOC for any repair
required by this AD to the Authorized
Representative for the Boeing DOA
Organization rather than the Designated
Engineering Representative.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, and
determined that air safety and the
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public interest require adopting the AD
with the changes described previously.
We have determined that these changes
will neither increase the economic
burden on any operator nor increase the
scope of the AD.
Costs of Compliance
This AD affects about 139 airplanes
worldwide. The following table
provides the estimated costs for U.S.
operators to comply with this AD.
ESTIMATED COSTS
Inspection test, per inspection
cycle.
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD. See the ADDRESSES section for
16:09 Mar 30, 2005
Parts
$65
None ..
6 (1 work hour per
slat, 6 slats per airplane.).
Authority for This Rulemaking
VerDate jul<14>2003
Average
labor
rate per
hour
Work
hours
Action
Jkt 205001
Number
of U.S.registered
airplanes
Cost per
airplane
$390, per inspection/
test cycle.
97
Fleet cost
$37,830, per inspection/test cycle
a location to examine the regulatory
evaluation.
the compliance times specified, unless the
actions have already been done.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Repetitive Inspections and Tests
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
2005–07–08 Boeing: Amendment 39–14032.
Docket No. FAA–2004–18876;
Directorate Identifier 2003–NM–254–AD.
Effective Date
(a) This AD becomes effective May 5, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 757–
200 and –200PF series airplanes, certificated
in any category, identified in Boeing Alert
Service Bulletin 757–57A0063, dated June
26, 2003.
Unsafe Condition
(d) This AD was prompted by a report of
damage to the No. 4 leading edge slat. We are
issuing this AD to prevent delamination of
the leading edge slats, possible loss of pieces
of the trailing edge wedge assembly during
flight, reduction of the reduced maneuver
and stall margins, and consequent reduced
controllability of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
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(f) Within 18 months after the effective
date of this AD: Do a detailed inspection and
an audible tap test of the upper and lower
skins of the trailing edge wedges on slats No.
2 through No. 4 inclusive and No. 7 through
No. 9 inclusive, for evidence of damage or
cracking, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 757–57A0063, dated June
26, 2003. Repeat the detailed inspection and
audible tap test thereafter at intervals not to
exceed 18 months.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Related Investigative and Corrective Actions
(g) If any damage or cracking is found
during any inspection or audible tap test
required by paragraph (f) of this AD: Before
further flight, do the related investigative
action, if applicable, and replace the affected
part with a new trailing edge wedge assembly
or repair the affected part, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 757–57A0063, dated
June 26, 2003. Accomplishing the
replacement terminates the repetitive
inspections and audible tap tests required by
paragraph (f) of this AD for that wedge
assembly only.
Actions Accomplished Previously
(h) Previous accomplishment of all of the
actions specified in the Accomplishment
Instructions of Boeing Service Bulletin 757–
57A0038, Revision 5, dated July 16, 1992; or
Revision 6, dated November 10, 1994; in
conjunction with the use of BMS 5–137
adhesive; is acceptable for compliance with
the inspection requirements of paragraph (f)
of this AD.
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Federal Register / Vol. 70, No. 61 / Thursday, March 31, 2005 / Rules and Regulations
Parts Installation
DEPARTMENT OF TRANSPORTATION
(i) As of the effective date of this AD, no
trailing edge wedge assembly having a part
number listed in the ‘‘Existing Part Number’’
column of the table in paragraph 2.C.3. of
Boeing Alert Service Bulletin 757–57A0063,
dated June 26, 2003, may be installed on any
airplane unless it has been inspected, tested,
and had any necessary corrective actions
accomplished in accordance with this AD.
Optional Terminating Action
(j) Replacing all trailing edge wedge
assemblies with new, improved wedge
assemblies in accordance with Part III of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 757–57A0063, dated June
26, 2003, terminates the requirements of
paragraph (f) of this AD.
Alternative Methods of Compliance
(AMOCs)
Material Incorporated by Reference
(l) You must use Boeing Alert Service
Bulletin 757–57A0063, dated June 26, 2003,
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. For copies of the service
information, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207. For information on
the availability of this material at the
National Archives and Records
Administration (NARA), call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
You may view the AD docket at the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washington,
DC.
Issued in Renton, Washington, on March
22, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–6259 Filed 3–30–05; 8:45 am]
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14 CFR Part 39
[Docket No. FAA–2004–18024; Directorate
Identifier 2003–NE–39–AD; Amendment 39–
14034; AD 2005–07–10]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
(1971) Limited, Bristol Engine Division
Model Viper Mk.601–22 Turbojet
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
Examining the AD Docket
The FAA is superseding an
existing airworthiness directive (AD) for
Rolls-Royce (1971) Limited, Bristol
Engine Division (RR) model Viper
Mk.601–22 turbojet engines. That AD
currently requires reducing the life of
certain 1st stage turbine rotor blades
from 7,000 hours time-in-service (TIS)
to 4,600 hours TIS, and provides a
drawdown schedule for blades that have
already exceeded the new reduced life
limit. This AD requires the same actions
but changes certain compliance times to
be in agreement with RR Alert Service
Bulletin (ASB) No. 72–A184, dated
January 2001. This AD results from
comments received on AD 2004–13–03,
that the AD is unnecessarily more
restrictive than the requirements in the
associated RR ASB No. 72–A184. We are
issuing this AD to prevent multiple
failures of 1st stage turbine rotor blades
that could result in a dual-engine
shutdown.
SUMMARY:
(k)(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
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.
BILLING CODE 4910–13–P
Federal Aviation Administration
This AD becomes effective May
5, 2005.
ADDRESSES: You can get the service
information identified in this proposed
AD from Rolls-Royce Limited, Bristol
Engines Division, Technical
Publications Department CLS–4, P.O.
Box 3, Filton, Bristol, BS34 7QE
England; telephone 117–979–1234, fax
117–979–7575.
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Ian
Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803–
5299; telephone (781) 238–7178; fax
(781) 238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
DATES:
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a proposed airworthiness directive (AD).
The proposed AD applies to Rolls-Royce
(1971) Limited, Bristol Engine Division
(RR) model Viper Mk.601–22 turbojet
engines. We published the proposed AD
in the Federal Register on October 29,
2004 (69 FR 63104). That action
proposed to require reducing the life of
certain 1st stage turbine rotor blades
from 7,000 hours TIS to 4,600 hours
TIS, provide a drawdown schedule for
blades that have already exceeded the
new reduced life limit, and change
certain compliance times to be in
agreement with RR ASB No. 72–A184,
dated January 2001.
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the DMS Docket Offices
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Office (telephone (800) 647–
5227) is located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the proposal or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
We estimate that 84 RR model Viper
Mk.601–22 turbojet engines installed on
airplanes of U.S. registry will be affected
by this AD. We estimate that no
additional labor cost will be incurred to
replace 1st stage turbine rotor blades
when done at time of engine overhaul.
A replacement set 1st stage turbine rotor
blades costs about $166,987. Based on
these figures, we estimate the total cost
of the AD to U.S. operators to be
$14,026,950.
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.
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[Federal Register Volume 70, Number 61 (Thursday, March 31, 2005)]
[Rules and Regulations]
[Pages 16403-16406]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6259]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18876; Directorate Identifier 2003-NM-254-AD;
Amendment 39-14032; AD 2005-07-08]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 757-200 and -200PF Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 757-200 and -200PF series airplanes. This AD
requires repetitive inspections and audible tap tests of the upper and
lower skins of the trailing edge wedges on certain slats, and related
investigative and corrective actions if necessary. This AD also
provides an optional terminating action for the repetitive inspections
and audible tap tests. This AD is prompted by a report of damage to the
No. 4 leading edge slat. We are issuing this AD to prevent delamination
of the leading edge slats, possible loss of pieces of the trailing edge
wedge assembly during flight, reduction of the reduced maneuver and
stall margins, and consequent reduced controllability of the airplane.
DATES: This AD becomes effective May 5, 2005.
The incorporation by reference of a certain publication listed in
the AD is approved by the Director of the Federal Register as of May 5,
2005.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207. You can examine this information 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.
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-2004-18876; the directorate
identifier for this docket is 2003-NM-254-AD.
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) 914-6590.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39
with an AD for certain Boeing Model 757-200 and -200PF series
airplanes. That action, published in the Federal Register on August 17,
2004 (69 FR 51015), proposed to require repetitive inspections and
audible tap tests of the upper and lower skins of the trailing edge
wedges on certain slats, and related investigative and corrective
actions if necessary. The proposed AD also provided an optional
terminating action for the repetitive inspections and audible tap
tests.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
submitted on the proposed AD.
Supportive Comment
One commenter supports the proposed AD.
Request To Correct Typographical Error in Applicability
One commenter requests that the typographical error in paragraph
(c), Applicability, of the proposed AD, be corrected. The Applicability
in the proposed AD states that the AD applies to Boeing Model 737-200
and -200F series airplanes, as listed in Boeing Alert Service Bulletin
757-57A0063, dated June 26, 2003. The commenter states that the
reference to Model 737-200 and -200F series airplanes should be
corrected to avoid confusion between the referenced service bulletin
and proposed AD.
We agree and the Applicability section of this AD has been
corrected to reference ``Boeing Model 757-200 and -200PF series
airplanes identified in Boeing Alert Service Bulletin 757-57A0063. * *
*'' We discovered this error after the proposed AD was published. We
find that our intent in the proposed AD was clear, as all other
references throughout the proposed AD were correct, and the referenced
service
[[Page 16404]]
bulletin applies to Boeing Model 757-200 and -200PF series airplanes.
Thus, we find no reason to re-open the comment period.
Request To Clarify Applicability
The Air Transport Association (ATA) states that its member airlines
concur with the intent of the proposed AD, but that the applicability
of the proposed AD is unclear. The commenter notes that actions
specified in the proposed AD overlap or duplicate the requirements of
AD 90-23-06, amendment 39-6794. The commenter also states that several
slat wedge configurations exist in in-service airplanes as a result of
AD 91-22-51, amendment 39-8129, and several other service bulletins
that address trailing edge wedges. The commenter contends that the
applicability of the proposed AD is unclear with respect to these
configurations, and recommends that we revise the proposed AD to
clearly state the applicability with respect to the various
configurations resulting from the aforementioned airworthiness
directives and service bulletins.
We do not agree that the applicability of this AD requires
revision. The applicability of this AD states that the AD applies to
Boeing Model 757-200 and -200PF series airplanes, certificated in any
category, identified in Boeing Alert Service Bulletin 757-57A0063,
dated June 26, 2003. The effectivity in that service bulletin is all
Boeing Model 757 series airplanes with line numbers 1 through 139
inclusive. This AD addresses line numbers 1 through 139 inclusive,
regardless of configuration. Also, the airplane applicability for AD
91-22-51 has different line numbers from those in this AD. The
applicability for that AD is Boeing Model 757 series airplanes, line
numbers 140 through 335. We have not changed this AD regarding this
issue.
Request To Give Credit for Actions Accomplished Previously
One commenter requests that the proposed AD be revised to indicate
that actions accomplished previously in accordance with Boeing Service
Bulletin 757-57A0038 or 757-57A0045 are acceptable for compliance with
the requirements of the proposed AD. The commenter states that the
actions described in those service bulletins have the same results as
the actions described in Boeing Alert Service Bulletin 757-57A0063,
dated June 26, 2003.
Service Bulletins With Similar Actions
----------------------------------------------------------------------------------------------------------------
As the appropriate
Service Bulletin-- Dated-- Is cited in-- source of service
information for--
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin 757- June 26, 2003.......... The proposed AD........ Inspecting, repairing,
57A0063. and replacing trailing
edge wedges.
Boeing Service Bulletin 757-57A0038, October 10, 1990....... AD 90-23-06, amendment Inspecting, repairing,
Revision 2. 39-6794. and replacing trailing
edge wedges.
Boeing Service Bulletin 757-57A0045.. October 16, 1991....... AD 91-22-51, amendment Repetitive detailed
39-8129. inspections of the
trailing edge wedges
of slats 1 through 4
and 7 through 10.
----------------------------------------------------------------------------------------------------------------
We agree that accomplishment of the actions specified in Boeing
Service Bulletin 757-57A0038, Revision 5, dated July 16, 1992, or
Revision 6, dated November 10, 1994, only, are acceptable for
compliance with the requirements of this AD. We do not agree that
accomplishment of the actions specified in Boeing Service Bulletin 757-
57A0045 is acceptable for compliance with the requirements of this AD.
As stated previously, the applicability of AD 91-22-51 is Boeing Model
757 series airplanes, line numbers 140 through 335 inclusive, and the
applicability of this AD is line numbers 1 through 139 inclusive.
We have included a new paragraph (h) in this AD, and reidentified
the subsequent paragraphs accordingly. Paragraph (h) specifies that
accomplishment of the actions in the Accomplishment Instructions of
Boeing Service Bulletin 757-57A0038, Revision 5 or Revision 6 only, in
conjunction with the use of BMS 5-137 adhesive, is acceptable for
compliance with the requirements of this AD.
Request To Revise Compliance Time for Repetitive Inspections and Tests
One commenter requests an extension of the compliance time from 18
months to 24 months for the repetitive detailed inspections and audible
tap tests of the upper and lower skins of the trailing edge wedges. The
commenter states that it performs maintenance checks (``C-checks'') on
its fleet every 24 months. The commenter also states that a compliance
time of 18 months would require special maintenance visits in addition
to the normally scheduled ``C-checks,'' and the associated costs and
downtime would be considerable. The commenter has reviewed its
maintenance program, and the subject slats are currently inspected
every 48 months. A review of the associated maintenance task cards did
not reveal any discrepancies. The commenter notes that this change to
the proposed AD would prevent operators from having to request approval
of an AMOC for the proposed AD.
We do not agree with the commenter's request to extend the
compliance time. In developing an appropriate compliance time for this
AD, we considered the urgency associated with the subject unsafe
condition, the manufacturer's recommended compliance time, and the
practical aspect of accomplishing the required inspections within a
period of time that corresponds to the normal scheduled maintenance
program for most affected operators. However, according to the
provisions of paragraph (k) of this AD, we may approve a request to
adjust the compliance time if the request includes data that prove that
the new compliance time would provide an acceptable level of safety.
Explanation of Additional Change to This AD
Since the publication of the proposed AD, Boeing has received a
Delegation Option Authorization (DOA). We have revised this AD to
delegate the authority to approve an AMOC for any repair required by
this AD to the Authorized Representative for the Boeing DOA
Organization rather than the Designated Engineering Representative.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the
[[Page 16405]]
public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
This AD affects about 139 airplanes worldwide. The following table
provides the estimated costs for U.S. operators to comply with this AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average Number of
labor U.S.-
Action Work hours rate per Parts Cost per airplane registered Fleet cost
hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection test, per inspection 6 (1 work hour per $65 None................. $390, per inspection/ 97 $37,830, per
cycle. slat, 6 slats per test cycle. inspection/test
airplane.). cycle
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-07-08 Boeing: Amendment 39-14032. Docket No. FAA-2004-18876;
Directorate Identifier 2003-NM-254-AD.
Effective Date
(a) This AD becomes effective May 5, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 757-200 and -200PF series
airplanes, certificated in any category, identified in Boeing Alert
Service Bulletin 757-57A0063, dated June 26, 2003.
Unsafe Condition
(d) This AD was prompted by a report of damage to the No. 4
leading edge slat. We are issuing this AD to prevent delamination of
the leading edge slats, possible loss of pieces of the trailing edge
wedge assembly during flight, reduction of the reduced maneuver and
stall margins, and consequent reduced controllability of 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.
Repetitive Inspections and Tests
(f) Within 18 months after the effective date of this AD: Do a
detailed inspection and an audible tap test of the upper and lower
skins of the trailing edge wedges on slats No. 2 through No. 4
inclusive and No. 7 through No. 9 inclusive, for evidence of damage
or cracking, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003.
Repeat the detailed inspection and audible tap test thereafter at
intervals not to exceed 18 months.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Related Investigative and Corrective Actions
(g) If any damage or cracking is found during any inspection or
audible tap test required by paragraph (f) of this AD: Before
further flight, do the related investigative action, if applicable,
and replace the affected part with a new trailing edge wedge
assembly or repair the affected part, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
57A0063, dated June 26, 2003. Accomplishing the replacement
terminates the repetitive inspections and audible tap tests required
by paragraph (f) of this AD for that wedge assembly only.
Actions Accomplished Previously
(h) Previous accomplishment of all of the actions specified in
the Accomplishment Instructions of Boeing Service Bulletin 757-
57A0038, Revision 5, dated July 16, 1992; or Revision 6, dated
November 10, 1994; in conjunction with the use of BMS 5-137
adhesive; is acceptable for compliance with the inspection
requirements of paragraph (f) of this AD.
[[Page 16406]]
Parts Installation
(i) As of the effective date of this AD, no trailing edge wedge
assembly having a part number listed in the ``Existing Part Number''
column of the table in paragraph 2.C.3. of Boeing Alert Service
Bulletin 757-57A0063, dated June 26, 2003, may be installed on any
airplane unless it has been inspected, tested, and had any necessary
corrective actions accomplished in accordance with this AD.
Optional Terminating Action
(j) Replacing all trailing edge wedge assemblies with new,
improved wedge assemblies in accordance with Part III of the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
57A0063, dated June 26, 2003, terminates the requirements of
paragraph (f) of this AD.
Alternative Methods of Compliance (AMOCs)
(k)(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 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
(l) You must use Boeing Alert Service Bulletin 757-57A0063,
dated June 26, 2003, 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. For
copies of the service information, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. For
information on the availability of this material at the National
Archives and Records Administration (NARA), call (202) 741-6030, or
go to https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.
You may view the AD docket at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-
401, Nassif Building, Washington, DC.
Issued in Renton, Washington, on March 22, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-6259 Filed 3-30-05; 8:45 am]
BILLING CODE 4910-13-P
