[Federal Register: August 31, 2007 (Volume 72, Number 169)]
[Proposed Rules]
[Page 50284-50288]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr31au07-20]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29061; Directorate Identifier 2006-NM-243-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-8-11, DC-8-
12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43
Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-50, -60, -
60F, -70, and -70F Series Airplanes; Model DC-9-10, -20, -30, -40, and
-50 Series Airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83
(MD-83), and DC-9-87 (MD-87) Airplanes; and Model MD-88 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain McDonnell Douglas airplanes. The
existing AD currently requires an initial
[[Page 50285]]
general visual or dye penetrant inspection, repetitive dye penetrant
inspections, and replacement, as necessary, of the rudder pedal
bracket. The existing AD also requires, for certain airplanes,
replacing the rudder pedal bracket assemblies with new, improved parts,
which would terminate the repetitive inspections. This proposed AD
would, for certain airplanes, reduce initial inspection thresholds,
remove an inspection option, and lengthen the repetitive inspection
intervals. This proposed AD results from reports of failures of the
captain's rudder pedal brackets before reaching the initial inspection
threshold identified in the existing AD. We are proposing this AD to
prevent failure of the rudder pedal bracket assembly, which could
result in the loss of rudder and braking control at either the
captain's or first officer's position.
DATES: We must receive comments on this proposed AD by October 15,
2007.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and
Service Management, Dept. C1-L5A (D800-0024) for service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5324; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2007-29061; Directorate Identifier 2006-NM-243-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or may
can visit http://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at http://
dms.dot.gov, or in person at the Docket Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The
Docket Operations office (telephone (800) 647-5527) is located on the
ground floor of the West Building at the street address stated in the
ADDRESSES section. Comments will be available in the AD docket shortly
after the Docket Management System receives them.
Discussion
On March 31, 2006, we issued AD 2006-07-25, amendment 39-14552 (71
FR 18201, April 11, 2006), for certain McDonnell Douglas Model DC-8-11,
DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-
8-43 airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-50, -
60, -60F, and -70 series airplanes; Model DC-9-10, -20, -30, -40, and -
50 series airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83
(MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes. That
AD requires an initial general visual or dye penetrant inspection,
repetitive dye penetrant inspections, and replacement, as necessary, of
the rudder pedal bracket. The existing AD also requires, for certain
airplanes, replacing the rudder pedal bracket assemblies with new,
improved parts, which would terminate the repetitive inspections. That
AD resulted from a report of numerous cracked rudder pedal brackets
found during inspections of certain affected airplanes. We issued that
AD to prevent failure of the rudder pedal bracket assembly, which could
result in the loss of rudder and braking control at either the
captain's or first officer's position.
Actions Since Existing AD Was Issued
Since we issued AD 2006-07-25, two Model MD-80 operators have
reported failures of the captain's rudder pedal brackets before
reaching the initial inspection threshold of 40,000 total landings
specified in AD 2006-07-25. One operator reported finding a crack in
the first officer's rudder pedal bracket at 34,000 landings. Lab
analysis of these parts verified that fatigue was the cause of the
failure. Boeing re-evaluated the current inspection interval and
determined that lowering the initial threshold to 25,000 total landings
is necessary for operators of Model DC-9-81 (MD-81), DC-9-82 (MD-82),
DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88
airplanes.
Boeing also determined that the general visual inspection for
cracks is no longer necessary because the eddy current and dye
penetrant inspections are adequate for Model DC-9-10, -20, -30, -40,
and -50 series airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-
83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes.
In addition, Boeing has lengthened the repetitive inspection interval
for the eddy current and any applicable dye penetrant inspection (also
called ``special detailed inspections'') for these airplanes from
intervals not to exceed 2,500 landings to intervals not to exceed 3,000
landings.
Clarification of Applicability
We have also clarified the applicability to include Model DC-8-71F,
DC-8-72F, and DC8-73F airplanes. These models were inadvertently
omitted from Table 1, paragraph (c), ``Applicability,'' of AD 2006-07-
25. However, these models were included in the effectivity of McDonnell
Douglas DC-8 Alert Service Bulletin A27-273, dated May 16, 1989, which
we referred to in AD 2006-07-25 as a source for identifying airplanes
affected by that AD.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin DC9-27A307, Revision
7, dated August 29, 2006. We referred to an earlier revision of this
same service bulletin (McDonnell Douglas DC-9 Alert
[[Page 50286]]
Service Bulletin A27-307, Revision 6, dated December 19, 1994) as the
appropriate source of service information for doing certain actions in
AD 2006-07-25.
The actions in Boeing Alert Service Bulletin DC9-27A307, Revision
7, are essentially the same as those in McDonnell Douglas DC-9 Alert
Service Bulletin A27-307, Revision 6. However, Boeing Alert Service
Bulletin DC9-27A307, Revision 7, revises certain inspection thresholds
and intervals. Revision 7 also removes a general visual inspection for
certain airplanes and, instead, specifies a special detailed
inspection. The special detailed inspection consists of either doing an
eddy current inspection for cracking of the rudder pedal bracket
assemblies and, if any crack is found, doing a penetrant inspection for
cracking; or doing the penetrant inspection for cracking of the rudder
pedal bracket assemblies. Revision 7 includes a definition of a special
detailed inspection.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2006-07-25 and would retain the requirements of the
existing AD. This proposed AD would also, for certain airplanes, reduce
certain initial inspection thresholds, remove an inspection option, and
lengthen certain repetitive inspection intervals.
Explanation of Changes to Existing AD
We have changed the parts cost for the replacement to reflect the
cost information in the current Boeing service information.
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
We have revised references to certain service information to more
accurately reflect the reference as cited on the service information
itself.
We have added a new paragraph (f) titled ``Service Information and
Airplane Categories'' to reduce the length of the references to both in
the AD itself. We have re-identified the paragraphs accordingly, and
revised this action to refer to the airplane categories rather than
list the models individually. We have also removed Note 2 of the
existing AD because the new paragraph (f) makes the contents of the
note unnecessary.
Costs of Compliance
There are about 1,840 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD. The replacements are
applicable only to Model DC-9-10, -20, -30, -40, and -50 series
airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and
DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes.
Estimated Costs
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Work Average labor Number of U.S.-
Action hours rate per hour Parts Cost per airplane registered airplanes Fleet cost
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General visual inspection 3 $80 None................. $240, per inspection 250.................. $60,000, per
(required by AD 2006-07-25). cycle. inspection cycle.
Dye penetrant (special detailed) 5 80 None................. $400, per inspection 946.................. $378,400, per
inspection (required by AD 2006- cycle. inspection cycle.
07-25).
Replacements (required by AD 2006- 9 80 $9,466............... $10,186.............. up to 946............ up to $9,635,956.
07-25).
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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.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
[[Page 50287]]
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14552 (71 FR 18201, April 11, 2006) and adding
the following new airworthiness directive (AD):
McDonnell Douglas: Docket No. FAA-2007-29061; Directorate Identifier
2006-NM-243-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by October
15, 2007.
Affected ADs
(b) This AD supersedes AD 2006-07-25.
Applicability
(c) This AD applies to the airplanes identified in Table 1 of
this AD, certificated in any category.
Table 1.--Applicability
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McDonnell Douglas-- As identified in--
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Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8- McDonnell Douglas DC-8
32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Alert Service
airplanes; Model DC-8-51, DC-8-52, DC-8-53, and Bulletin A27-273,
DC-8-55 airplanes; Model DC-8F-54 and DC-8F-55 Revision 5, dated
airplanes; Model DC-8-61, DC-8-62, and DC-8-63 February 18, 1993.
airplanes; Model DC-8-61F, DC-8-62F, and DC-8-
63F airplanes; Model DC-8-71, DC-8-72, and DC-8-
73 airplanes; Model DC-8-71F, DC-8-72F, and DC-
8-73F airplanes.
Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9- Boeing Alert Service
15, and DC-9-15F airplanes; Model DC-9-21 Bulletin DC9-27A307,
airplanes; Model DC-9-31, DC-9-32, DC-9-32 (VC- Revision 7, dated
9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, and August 29, 2006.
DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41
airplanes; Model DC-9-51 airplanes; Model DC-9-
81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83),
and DC-9-87 (MD-87) airplanes; and Model MD-88
airplanes.
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Unsafe Condition
(d) This AD results from reports of failures of the captain's
rudder pedal brackets before reaching the initial inspection
threshold identified in AD 2006-07-25. We are issuing this AD to
prevent failure of the rudder pedal bracket assembly, which could
result in the loss of rudder and braking control at either the
captain's or first officer's position.
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 and Airplane Categories
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of the applicable service bulletin
identified in Table 2 of this AD. The term ``airplane category,'' as
used in this AD, means the category identified in Table 2 of this
AD.
Table 2.--Service Information and Airplane Categories
----------------------------------------------------------------------------------------------------------------
Called
For Model-- airplane Use this service bulletin--
category--
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(1) DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, 1 McDonnell Douglas DC-8 Alert Service
DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-51, Bulletin A27-273, Revision 1, dated
DC-8-52, DC-8-53, and DC-8-55 airplanes; Model DC-8F-54 May 16, 1989; or Revision 5, dated
and DC-8F-55 airplanes; Model DC-8-61, DC-8-62, and DC-8- February 18, 1993.
63 airplanes; Model DC-8-61F, DC-8-62F, and DC-8-63F
airplanes; Model DC-8-71, DC-8-72, and DC-8-73 airplanes.
(2) DC-8-71F, DC-8-72F, and DC-8-73F airplanes........... 2 .....................................
(3) DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9- 3 McDonnell Douglas DC-9 Alert Service
15F airplanes; Model DC-9-21 airplanes; Model DC-9-31, Bulletin A27-307, Revision 1, dated
DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, May 16, 1989; or Boeing Alert
DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC- Service Bulletin DC9-27A307,
9-41 airplanes; Model DC-9-51 airplanes. Revision 7, dated August 29, 2006
(after the effective date of this
AD, only Revision 7 may be used).
(4) DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), 4 .....................................
and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes.
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Requirements of AD 2006-07-25
Initial Inspection Threshold
(g) For airplane categories 1, 3, and 4, prior to the
accumulation of 40,000 total landings or within 30 days after July
5, 1989 (the effective date of AD 89-14-02, amendment 39-6245, which
was superseded by AD 2006-07-25), whichever occurs later: Perform
either a general visual inspection, dye penetrant inspection, or
special detailed inspection (eddy current with dye penetrant or just
dye penetrant), as applicable, for cracking of the captain's and
first officer's rudder pedal bracket, part numbers (P/N) 5616067 and
5616068, respectively, in accordance with the Accomplishment
Instructions of the applicable service bulletin specified in Table 2
of this AD. After the effective date of this AD, only the special
detailed inspection specified in Boeing Alert Service Bulletin DC9-
27A307, Revision 7, may be used for airplanes identified in Revision
7. For airplane category 4: Do the inspection required by this
paragraph until the inspection required by paragraph (j) of this AD
is accomplished.
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
(1) If an initial general visual inspection is accomplished, and
no crack is found, perform a dye penetrant inspection of the rudder
pedal bracket assembly within 180 days after the general visual
inspection, and
[[Page 50288]]
thereafter accomplish dye penetrant inspections at intervals not to
exceed 12 months or 2,500 landings, whichever occurs earlier. For
airplane categories 3 and 4, repeat at this interval until the
inspection required by paragraph (k) of this AD is accomplished.
(2) If an initial dye penetrant inspection is accomplished, and
no crack is found, accomplish repetitive dye penetrant inspections
at intervals not to exceed 12 months or 2,500 landings, whichever
occurs earlier. For airplane categories 3 and 4, repeat at this
interval until the inspection required by paragraph (k) of this AD
is accomplished.
(3) If an initial special detailed inspection is accomplished
after the effective date of this AD, and no crack is found, repeat
the inspection in accordance with paragraph (k) of this AD.
Corrective Action
(h) Except as provided by paragraph (l) of this AD: If any crack
is detected during any inspection required by paragraph (g) or (j)
of this AD, before further flight, remove and replace the rudder
pedal bracket assembly in accordance with the service bulletin.
Prior to the accumulation of 40,000 total landings after replacement
with the new part, resume the repetitive inspections in accordance
with paragraph (g) or (k) of this AD, as applicable. Doing the
action required by paragraph (l) of this AD terminates the
requirements of this paragraph for airplane category 4.
Terminating Action for Certain Airplanes
(i) For airplane categories 3 and 4: Do the actions in
paragraphs (i)(1) and (i)(2) of this AD in accordance with the
Accomplishment Instructions of the service bulletin.
(1) Before the accumulation of 75,000 total landings on the
captain's rudder pedal bracket assembly, P/N 5616067-501, or within
60 months after May 16, 2006, whichever occurs later: Remove the
rudder pedal bracket assembly and replace it with new, improved P/N
5962903-501. Accomplishment of the replacement terminates the
repetitive inspections of the captain's rudder pedal bracket
assembly required by paragraphs (g), (h), (j), (k), and (l) of this
AD.
(2) Before the accumulation of 75,000 total landings on the
first officer's rudder pedal bracket assembly, P/N 5616068-501, or
within 60 months after May 16, 2006, whichever occurs later: Remove
the rudder pedal bracket assembly and replace it with new, improved
P/N 5962904-501. Accomplishment of the replacement terminates the
repetitive inspections of the first officer's rudder pedal bracket
assembly required by paragraphs (g), (h), (j), (k), and (l) of this
AD.
New Requirements of This AD
Revised Initial Inspection at Reduced Threshold for Certain
Airplanes
(j) For airplane categories 2 and 4, at the applicable time
specified in paragraph (j)(1), (j)(2) or (j)(3) of this AD: Do a
special detailed inspection for cracking of the captain's and first
officer's rudder pedal bracket, part numbers (P/N) 5616067 and
5616068, respectively, in accordance with the service bulletin.
Doing this inspection terminates the inspection requirements of
paragraphs (g) and (h) of this AD for airplane category 4.
(1) For category 2 airplanes: Before the accumulation of 40,000
total landings or within 30 days after the effective date of this
AD, whichever occurs later.
(2) For category 4 airplanes that have accumulated fewer than
25,000 total landings as of the effective date of this AD: Before
the accumulation of 25,000 total landings, or within 3,000 landings
after the effective date of this AD, whichever occurs later.
(3) For category 4 airplanes that have accumulated 25,000 or
more total landings as of the effective date of this AD, do the next
inspection at the applicable time in paragraph (j)(3)(i) or
(j)(3)(ii) of this AD.
(i) For category 4 airplanes on which the corrective action
specified in paragraph (h) of this AD has not been accomplished, do
the inspection within 3,000 landings after the effective date of
this AD.
(ii) For category 4 airplanes on which the corrective action
required by paragraph (h) of this AD has been accomplished, do the
inspection at the earlier of the following: The next repetitive
interval required by paragraph (h) of this AD; 40,000 total landings
after doing the corrective action required by paragraph (h) of this
AD; or 3,000 landings after the effective date of this AD.
Repetitive Inspections at Revised Interval for Certain Airplanes
(k) For airplane categories 3 and 4: Repeat the special detailed
inspection required by paragraph (g) or (j) of this AD thereafter at
intervals not to exceed 3,000 landings. Doing the first repetitive
inspection required by this paragraph terminates the repetitive
inspection requirements of paragraph (g) of this AD for airplane
categories 3 and 4.
Corrective Action Including Reduced Inspection Threshold for
Certain Airplanes
(l) For airplane category 4: If any crack is detected during any
inspection required by paragraph (g), (j), or (k) of this AD: Before
further flight, remove and replace the rudder pedal bracket assembly
in accordance with the service bulletin. Before the accumulation of
25,000 total landings after replacement with the new part, resume
the repetitive inspections in accordance with paragraph (k) of this
AD. Doing the action in this paragraph terminates the requirements
of paragraph (h) of this AD for airplane category 4.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Los Angeles Aircraft Certification Office,
Transport Airplane Directorate, FAA, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs, approved previously in accordance with AD 2006-07-25,
amendment 39-14552; and AD 89-14-02, amendment 39-6245; are approved
as AMOCs for the corresponding requirements of this AD.
Issued in Renton, Washington, on August 17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-17287 Filed 8-30-07; 8:45 am]
BILLING CODE 4910-13-P