[Federal Register Volume 73, Number 221 (Friday, November 14, 2008)]
[Rules and Regulations]
[Pages 67368-67372]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-25761]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0414; Directorate Identifier 2007-NM-095-AD; 
Amendment 39-15714; AD 2008-22-17]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, and 747SR Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to certain Boeing Model 747 series airplanes. That AD 
currently requires repetitive inspections for cracking and corrosion of 
all exposed surfaces of the carriage spindles (including the inner bore 
and aft links) of the trailing edge flaps, and additional inspection 
and corrective action if necessary. That AD also currently requires 
repetitive overhaul of the carriage spindle and aft link, which 
terminates the repetitive inspections. This new AD adds a repetitive 
inspection to detect broken parts, and revises the overhaul threshold 
and repetitive intervals. This AD results from analysis that showed 
additional inspections should be done to prevent the loss of a flap, 
and that the flight-hour-based interval should be revised to a flight-
cycle-based interval, because the greatest loads on the spindles happen 
during takeoff and landing. We are issuing this AD to detect and 
correct failed carriage spindles or aft links of the inboard or 
outboard trailing edge flaps. Such failure could cause the flap to 
depart the airplane, reducing the flightcrew's ability to maintain the 
safe flight and landing of the airplane.

DATES: This AD becomes effective December 19, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of December 19, 
2008.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707,

[[Page 67369]]

Seattle, Washington 98124-2207; telephone 206-544-9990; fax 206-766-
5682; e-mail [email protected]; Internet http://www.myboeingfleet.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6443; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 90-17-19, amendment 39-
6705 (55 FR 33280, August 15, 1990). The existing AD applies to certain 
Boeing Model 747 series airplanes. That NPRM was published in the 
Federal Register on April 28, 2008 (73 FR 22845). That NPRM proposed to 
retain the requirements of the existing AD but to add a repetitive 
inspection to detect broken parts, and revise the overhaul threshold 
and repetitive intervals.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Support for the NPRM

    Boeing has reviewed the NPRM and concurs with the contents of the 
proposed rule. Northwest Airlines (NWA) has no technical objection to 
the AD.

Requests To Revise Inspection Threshold

    The Hong Kong Civil Aviation Department, and Air Transport 
Association (ATA), on behalf of its member NWA, request that we revise 
the inspection threshold for the inspection for broken parts proposed 
in paragraph (i) of the NPRM. The commenters point out that the NPRM 
stated the first inspection should be done at the earlier of 12 months 
or 400 flight cycles after the effective date of the AD; however, 
Boeing Service Bulletin 747-27-2280, Revision 6, dated February 14, 
2008, specifies doing that inspection at the later of those two times.
    We agree with the commenters. It was our intent that the compliance 
threshold should match that of the Boeing Service Bulletin 747-27-2280, 
Revision 6. We have revised paragraph (i) of the AD as requested.

Request To Clarify Compliance Times

    ATA on behalf of NWA, requests that we revise paragraph (j), 
``Repetitive Overhauls,'' of the NPRM to clarify the compliance 
threshold for the initial overhaul for carriage assemblies previously 
overhauled in accordance with the requirements of AD 90-17-19. NWA 
requests that we specify that the compliance threshold is measured from 
the completion of the overhaul mandated by AD 90-17-19 for carriages/
assemblies previously overhauled.
    We agree that the compliance times can be clarified, although we do 
not agree that it is necessary to change the AD in this regard. 
Paragraph (j) of the NPRM specifies doing the initial overhaul at the 
later of the applicable thresholds specified in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-27-2280, Revision 6, 
dated February 14, 2008; or 48 months after the effective date of the 
AD. Paragraph 1.E. of the service bulletin includes notes (a) and (e). 
Note (a) states, ``Compliance Time and Repeat Interval applies to each 
new or overhauled carriage or aft link from the time it enters service, 
regardless of whether the part is removed and installed on another 
airplane.'' Note (e) states, ``The initial overhaul must be 
accomplished prior to terminating the repetitive overhauls at the 
compliance times specified in FAA AD 90-17-19.'' These notes provide 
the information requested by the commenter. It is the intent of this 
new AD that if the initial or repetitive overhaul required by AD 90-17-
19 is due prior to ``48 months after the effective date of this AD,'' 
the compliance time for the initial carriage overhaul will not be 
affected by the new requirements of this AD. However, if the initial or 
repetitive carriage overhaul required by AD 90-17-19 is due subsequent 
to ``48 months after the effective date of this AD,'' the required 
carriage overhauls are governed by the new compliance times of this AD. 
Specifically, the compliance time for carriages with sleeved journals 
is to accomplish the initial overhaul within 6000 flight cycles or 8 
years, whichever occurs first, since new or since completion of the 
overhaul mandated by AD 90-17-19; and the compliance time for carriages 
with chrome-plated forward and aft journals is to accomplish the 
initial overhaul within 9000 flight cycles or 8 years, whichever occurs 
first, since new or since completion of the overhaul mandated by AD 90-
17-19. We have not changed the AD in this regard.

Request To Revise Optional Terminating Action

    Japan Airlines (JAL) requests that we refer to the latest aft 
links. JAL explains that the latest aft links do not require a repeat 
overhaul, and points out that the latest aft links are not shown in 
Boeing Service Bulletin 747-27-2371, dated December 20, 2000 (we 
referred to this service bulletin in paragraph (k) of the NPRM as the 
source of service information for the optional terminating action of 
replacing the existing 4340M aft link with a new corrosion resistant 
steel (CRES) aft link). JAL states that the latest aft links are shown 
in paragraph 3.B.5. of Boeing Service Bulletin 747-27-2280, Revision 6, 
dated February 14, 2008.
    We agree that the newest aft links do not require a repeat overhaul 
and that a note in paragraph 3.B.5. of Boeing Service Bulletin 747-27-
2280, Revision 6, refers to these links. Therefore, we have revised 
paragraph (k) of this AD to state that replacing the existing 4340M aft 
link with a new CRES aft link in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 747-27-2371, dated December 20, 
2000, or with an aft link specified in paragraph 3.B.5. of the 
Accomplishment Instructions of Boeing Service Bulletin 747-27-2280, 
Revision 6, dated February 14, 2008, terminates the repetitive 
inspection requirements of paragraph (f) of this AD and the repetitive 
overhaul requirements of paragraphs (g) and (j) of this AD for that aft 
link only.

Request To Revise Repetitive Intervals

    All Nippon Airways (ANA) requests that we use the results of a 
Boeing analysis, using ANA flight data as a basis, to change intervals 
in the NPRM for Boeing Model 747-400D series airplanes, or provide the 
intervals as an alternative method of compliance (AMOC). ANA states 
that it operates five Boeing Model 747-400 series airplanes, for which 
the maximum takeoff weight

[[Page 67370]]

(MTOW) is 899,600 pounds, and 11 Boeing Model 747-400D series airplanes 
for which the MTOW is 599,600 pounds. ANA believes that the loads on 
the spindles must be smaller for the Model 747-400D series airplanes 
because of the difference between the takeoff and landing weights. ANA 
requests that Boeing develop for Model 747-400D series airplanes 
different repetitive intervals for the flap carriage overhaul and the 
general visual inspection. ANA makes this request because the 
repetitive flap carriage overhaul must be done every two to three C-
checks (3 to 4.5 years) and the general visual inspection must be done 
every 2 months, thus requiring a lot of manpower and costs. ANA 
provided no analysis to justify this requested increase.
    We disagree with the request to change the AD to include revised 
intervals for Boeing Model 747-400D series airplanes. The intervals for 
inspection proposed in the NPRM were based on analysis provided by the 
manufacturer. In the absence of any analysis showing the differences in 
landing weights for these spindles, there is no evidence that 
increasing the intervals would provide an acceptable level of safety. 
However, as ANA noted, under the provisions of paragraph (m) of the AD, 
we will consider requests for approval of an AMOC if sufficient data 
are submitted to substantiate that the change to the intervals would 
provide an acceptable level of safety. We have not changed the AD in 
this regard.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Costs of Compliance

    There are about 925 airplanes of the affected design in the 
worldwide fleet, which includes 160 airplanes of U.S. registry. The 
following table provides the estimated costs for U.S. operators to 
comply with this AD. The average labor rate is $80 per work hour.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
              Action                      Work hours        Parts     Cost per airplane          Fleet cost
----------------------------------------------------------------------------------------------------------------
 Inspection and overhaul (required   Between 120 and 140,       $0   Between $9,600 and     Between $1,536,000
 by AD 90-17-19).                    per flap per cycle.             $11,200, per flap      and $1,792,000, per
                                                                     per overhaul cycle.    flap per cycle.
 Repetitive inspection for broken    2, per inspection           0   $160, per inspection   $25,600, per
 parts (new action).                 cycle.                          cycle.                 inspection cycle.
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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 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 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, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-6705 (55 FR 33280, August 15, 1990) and by adding 
the following new airworthiness directive (AD):

2008-22-17 Boeing: Amendment 39-15714. Docket No. FAA-2008-0414; 
Directorate Identifier 2007-NM-095-AD.

Effective Date

    (a) This AD becomes effective December 19, 2008.

Affected ADs

    (b) This AD supersedes AD 90-17-19.

Applicability

    (c) This AD applies to all Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, and 747SR series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from analysis that showed that additional 
inspections should be done to prevent the loss of a flap, and that 
the flight-hour-based interval should be revised to a flight-cycle-
based interval, because the greatest loads on the spindles happen 
during takeoff and landing. We are issuing this AD to detect and 
correct failed carriage spindles or aft links of the inboard or 
outboard trailing edge flaps. Such failure could cause the flap to 
depart the airplane, reducing the flightcrew's ability to maintain 
the safe flight and landing of the airplane.

[[Page 67371]]

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.

Requirements of AD 90-17-19

Repetitive Inspections

    (f) For all airplanes except those airplanes on which the 
repetitive overhauls required by paragraph B. of AD 90-17-19 are 
being accomplished as of the effective date of this AD: Prior to the 
accumulation of 30,000 flight hours or 8 years on each new or 
previously overhauled flap carriage spindle, whichever occurs first, 
remove the aft link and thrust collars from the trailing edge flaps' 
carriage spindles and perform a detailed inspection of all exposed 
surfaces of the carriage spindles, including inner bore, and aft 
links to detect cracking and corrosion, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 747-27-2280, 
Revision 3, dated November 30, 1989.

    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.''

    (1) If no cracking or corrosion is found, repeat the inspections 
required by paragraph (f) of this AD at intervals not to exceed 12 
months until the carriage spindles are overhauled in accordance with 
paragraph (g) of this AD.
    (2) If a cracked carriage spindle or aft link is found, prior to 
further flight, replace the part(s) in accordance with the service 
bulletin.
    (3) If corrosion is found on any part of the carriage spindle/
aft link assembly, but not on the other assembly on the same flap, 
perform a repetitive general visual inspection in accordance with 
the service bulletin at intervals not to exceed 2 months. Overhaul 
or replace corroded parts in accordance with the service bulletin 
within 36 months after detection of the corrosion.
    (4) If corrosion is found on any part of both carriage spindle/
aft link assemblies on the same flap, prior to further flight, 
overhaul or replace the part(s) in accordance with the service 
bulletin or repair in accordance with the procedures specified in 
paragraph (m) of this AD.

    Note 2: 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.''

Initial and Repetitive Overhauls

    (g) For all airplanes: Prior to the accumulation of 8 years or 
30,000 flight hours on any new or previously overhauled flap 
carriage spindle, whichever occurs later, remove the carriage 
spindle and aft link, and overhaul in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 747-27-2280, 
Revision 3, dated November 30, 1989. Repeat the overhaul thereafter 
at intervals not to exceed 8 years or 30,000 flight hours, whichever 
occurs earlier. Accomplishment of initial overhaul required by this 
paragraph terminates the requirements of paragraph (f) of this AD.

New Requirements of This AD

Terminating Requirements

    (h) The actions specified in paragraphs (i) and (j) of this AD 
must be accomplished in their entirety, at the specified compliance 
times, to terminate the requirements of paragraphs (f) and (g) of 
this AD. There is no terminating action for the requirements of 
paragraphs (i) and (j) of this AD.

Repetitive Inspection for Broken Parts

    (i) For all airplanes: Within 12 months or 400 flight cycles 
after the effective date of this AD, whichever occurs later, do a 
general visual inspection of all eight carriage spindles and aft 
links to detect a broken carriage spindle or broken aft link, and do 
all applicable corrective actions before further flight. Repeat the 
inspection thereafter at intervals not to exceed 400 flight cycles. 
Do all actions in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 747-27-2280, Revision 6, dated February 14, 
2008. For airplanes identified in Note (d) of Table 1 in paragraph 
1.E., ``Compliance,'' of Boeing Service Bulletin 747-27-2280, 
Revision 6, dated February 14, 2008, the initial compliance time and 
repetitive interval for a flap may be extended to 1,000 flight 
cycles when new carriages are installed at both the inboard and 
outboard carriage locations on the flap.

Repetitive Overhauls

    (j) For all airplanes: At the later of the times specified in 
paragraph (j)(1) or (j)(2) of this AD, remove the carriage spindle 
and aft link, and overhaul in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 747-27-2280, Revision 6, 
dated February 14, 2008. Repeat the overhaul thereafter at the 
applicable repeat interval specified in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-27-2280, Revision 6, 
dated February 14, 2008.
    (1) The applicable threshold specified in paragraph 1.E. 
``Compliance,'' of Boeing Service Bulletin 747-27-2280, Revision 6, 
dated February 14, 2008.
    (2) Within 48 months after the effective date of this AD.

Optional Terminating Action

    (k) For Groups 1 and 3 airplanes identified in Boeing Service 
Bulletin 747-27-2280, Revision 6, dated February 14, 2008: Replacing 
the existing 4340M aft link with a new corrosion resistant steel 
(CRES) aft link in accordance with the Accomplishment Instructions 
of Boeing Service Bulletin 747-27-2371, dated December 20, 2000, or 
with an aft link specified in paragraph 3.B.5. of the Accomplishment 
Instructions of Boeing Service Bulletin 747-27-2280, Revision 6, 
dated February 14, 2008, terminates the repetitive inspection 
requirements of paragraph (f) of this AD, and the repetitive 
overhaul requirements of paragraphs (g) and (j) of this AD for that 
aft link only. The repetitive inspections for broken parts required 
by paragraph (i) of this AD cannot be terminated.

Credit for Actions Done Using Previous Revision of Service Bulletin

    (l) Actions done before the effective date of this AD in 
accordance with Boeing Service Bulletin 747-27-2280, Revision 4, 
dated April 26, 2001, are acceptable for compliance with the 
corresponding requirements of paragraphs (f) and (g) of this AD. 
Actions done before the effective date of this AD in accordance with 
Boeing Service Bulletin 747-27-2280, Revision 5, dated April 5, 
2007, are acceptable for compliance with the corresponding 
requirements of paragraphs (i) and (j) of this AD.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, ATTN: Gary Oltman, Aerospace Engineer, Airframe Branch, ANM-
120S, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; 
telephone (425) 917-6443; fax (425) 917-6590; has the authority to 
approve AMOCs for this AD, if requested using 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 90-17-19 are 
approved as AMOCs for the corresponding provisions of this AD.
    (4) Adjustments to the compliance times approved previously in 
accordance with AD 90-17-19 are not approved for the corresponding 
provisions of this AD.
    (5) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.

Material Incorporated by Reference

    (n) You must use the applicable service information identified 
in Table 1 of this AD to perform the actions that are required by 
this AD, unless the AD specifies otherwise.

[[Page 67372]]

If you accomplish the optional terminating actions specified by this 
AD, you must use the service information identified in Table 2 of 
this AD to perform those actions, unless the AD specifies otherwise.

Table 1--Material Incorporated by Reference for Actions Required in this
                                   AD
------------------------------------------------------------------------
                                       Revision
          Service Bulletin              level              Date
------------------------------------------------------------------------
Boeing Service Bulletin 747-27-2280.          3  Nov. 30, 1989.
Boeing Service Bulletin 747-27-2280.          6  Feb. 14, 2008.
------------------------------------------------------------------------

    Boeing Service Bulletin 747-27-2280, Revision 3, dated November 
30, 1989, contains the following effective pages:

------------------------------------------------------------------------
                                       Revision
              Page No.               level shown    Date shown on page
                                       on page
------------------------------------------------------------------------
1-26...............................            3  Nov. 30, 1989.
27-29..............................            2  Mar. 23, 1989.
------------------------------------------------------------------------


Table 2--Material Incorporated by Reference for the Optional Terminating
                            Action in this AD
------------------------------------------------------------------------
        Service Bulletin            Revision level           Date
------------------------------------------------------------------------
Boeing Service Bulletin 747-27-   6................  Feb. 14, 2008.
 2280.
Boeing Service Bulletin 747-27-   Original.........  Dec. 20, 2000.
 2371.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of these documents in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207; telephone 206-544-9990; fax 206-766-5682; e-
mail [email protected]; Internet https://www.myboeingfleet.com; for a 
copy of this service information.
    (3) You may review copies of the service information that is 
incorporated by reference at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 20, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-25761 Filed 11-13-08; 8:45 am]
BILLING CODE 4910-13-P