[Federal Register Volume 71, Number 96 (Thursday, May 18, 2006)]
[Proposed Rules]
[Pages 28827-28831]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-7559]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20080; Directorate Identifier 2003-NM-193-AD]
RIN 2120-AA64


Airworthiness Directives; Various Aircraft Equipped With 
Honeywell Primus II RNZ-850/-851 Integrated Navigation Units

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

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

-----------------------------------------------------------------------

SUMMARY: The FAA is revising an earlier NPRM for an airworthiness 
directive (AD) that applies to various aircraft equipped with a 
Honeywell Primus II RNZ-850/-851 Integrated Navigation Unit (INU). The 
original NPRM would have superseded an existing AD that, as one 
alternative for compliance, provides for a one-time inspection to 
determine whether a certain modification has been installed on the 
Honeywell Primus II NV850 Navigation Receiver Module (NRM), which is 
part of the INU. In lieu of accomplishing this inspection, and for 
aircraft found to have an affected NRM, the existing AD provides for 
revising the aircraft flight manual to include new limitations for 
instrument landing system approaches. The original NPRM proposed to 
require inspecting to determine whether certain other modifications 
have been done on the NRM; and doing related investigative, corrective, 
and other specified actions, as applicable. The original NPRM resulted 
from reports of erroneous glideslope indications on certain aircraft 
equipped with subject INUs. This new action revises the original NPRM 
by describing further modifications to address additional anomalies. We 
are proposing this supplemental NPRM to ensure that the flightcrew has 
an accurate glideslope deviation indication. An erroneous glideslope 
deviation indication could lead to the aircraft making an approach off 
the glideslope, which could result in impact with an obstacle or 
terrain.

DATES: We must receive comments on this supplemental NPRM by June 12, 
2006.

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: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Honeywell Aerospace Electronic Systems, CES--Phoenix, P.O. 
Box 2111, Phoenix, Arizona 85036-1111, for service information 
identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: J. Kirk Baker, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5345; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

[[Page 28828]]

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2005-20080; Directorate Identifier 2003-NM-193-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
supplemental NPRM. We will consider all comments received by the 
closing date and may amend this supplemental NPRM in light of those 
comments.
    We will post all comments submitted, 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 supplemental NPRM. 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 you 
may 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 Management Facility offices 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in ADDRESSES. Comments will be available in the 
AD docket shortly after the Docket Management System receives them.

Discussion

    We proposed to amend part 39 of the Federal Aviation Regulations 
(14 CFR part 39) with a notice of proposed rulemaking (NPRM) for an AD 
(the ``original NPRM'') for various aircraft equipped with a Honeywell 
Primus II RNZ-850/-851 Integrated Navigation Unit (INU). The original 
NPRM proposed to supersede AD 2003-04-06, amendment 39-13054 (68 FR 
8539, February 24, 2003), which applies to various aircraft equipped 
with the subject INU. AD 2003-04-06 stated that it was considered 
``interim action'' because the manufacturer was developing final 
corrective modifications for the unsafe condition specified in AD 2003-
04-06; and that we might consider further rulemaking when those 
modifications were released. The original NPRM followed from the 
release of those modifications. The original NPRM was published in the 
Federal Register on January 19, 2005 (70 FR 2982). The original NPRM 
proposed to require inspecting to determine whether certain other 
modifications have been done on the Honeywell Primus II NV850 
Navigation Receiver Module (NRM), which is part of the subject INU; and 
doing related investigative, corrective, and other specified actions, 
as applicable. The original NPRM resulted from reports of erroneous 
glideslope indications on certain aircraft equipped with subject INUs. 
That condition, if not corrected, could lead to the aircraft making an 
approach off the glideslope, which could result in impact with an 
obstacle or terrain.

Actions Since Original NPRM Was Issued

    Since we issued the original NPRM, there have been reports of 
additional anomalies during instrument landing system (ILS) landings on 
several Empresa Brasileira de Aeronautica S.A. (EMBRAER) airplanes 
equipped with subject INUs. Reports specified that the localizer 
deviation displayed by the INU changed quickly from a centered position 
to a full-scale deviation for a few seconds, then was flagged as 
invalid data. Honeywell has issued service information to address such 
ILS anomalies.

Relevant Service Information Specified in Original NPRM

    We have reviewed Honeywell Service Bulletin 7510100-34-A0035, dated 
July 11, 2003, which describes procedures for inspecting the NRM to 
determine whether Mod L has been done. If Mod L has not been done, the 
service bulletin specifies re-identifying the NRM with a new part 
number. If Mod L has been done, the service bulletin specifies 
inspecting to determine if Mod N, P, or R has also been done. (Mod N, 
P, and R test the NRM for discrepant signals.) If any of those mods has 
been done, the specified actions are replacing the existing 
modification plates on the NRM and INU with new plates bearing new part 
numbers. If Mod L has been done, but neither Mod N, P, nor R has been 
done, the service bulletin specifies doing further investigative 
actions and corrective actions in accordance with Honeywell Service 
Bulletin 7510100-34-A0034, dated February 28, 2003, then replacing the 
existing modification plates on the NRM and INU with new plates bearing 
new part numbers.
    Honeywell Service Bulletin 7510100-34-A0034 describes procedures 
for inspecting to determine the NRM part number and marking the 
modification plates of the NRM and INU accordingly. This service 
bulletin also describes procedures for a related investigative action 
if neither Mod N nor P is marked, which consists of testing the INU for 
discrepant signals. If any discrepant signal is detected, corrective 
action consists of replacing the unit with a new or modified INU. 
Honeywell Service Bulletin 7510100-34-A0034 refers to Honeywell Service 
Bulletin 7510134-34-A0016, currently at Revision 001, dated March 4, 
2003, as an additional source of service information for re-identifying 
the INU.

New Relevant Service Information

    We have reviewed Honeywell Service Bulletin 7510100-34-0037, dated 
July 8, 2004. The service bulletin describes procedures for replacing 
the NRM, which is part of the subject INU, with an NRM that is at Mod 
T. Service Bulletin 7510100-34-0037 also specifies Honeywell Service 
Bulletin 7510134-34-0018, dated July 8, 2004, as an additional source 
of service information for modifying the NRM to the ``Mod T'' 
configuration.
    We have reviewed Honeywell Service Bulletin 7510134-34-0018. The 
service bulletin describes procedures for determining the part number 
of a certain circuit card assembly (CCA) inside the NRM; replacing the 
RF absorber in the CCA, if necessary, with an improved RF absorber 
having a different part number and marking the appropriate revision 
letter on the CCA; and marking the NRM as Mod T.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

Comments

    We have considered the following comments on the original NPRM.

Request for Increased Compliance Time

    One commenter, Express Jet, requests that we extend the compliance 
time. The commenter states it has already returned about 106 suspect 
units to Honeywell for modification. Express Jet asserts that program 
data collected for 475,000 flight hours for the modified units show no 
occurrence of the described anomalies. Express Jet further states it 
has a large number of airplanes still to be inspected and modified and 
asserts that accomplishing the inspections and modifications within

[[Page 28829]]

the specified 12 months will be very cumbersome. Express Jet requests 
that we extend the compliance time to 24 months.
    We agree with this request. The revisions specified in paragraph 
(h) of the proposed AD for the Limitations section of the aircraft 
flight manual (AFM) will continue to be required until all aircraft 
have been modified. Further, Express Jet has submitted data showing no 
occurrence of the described anomalies for any of its modified units. 
Therefore, we have determined that these combined factors demonstrate 
that extending the compliance time as requested will pose no increased 
risk to affected aircraft. Accordingly, we have revised the 12-month 
compliance time specified in paragraph (j) of the original NPRM to 24 
months in this supplemental NPRM.

Request for Clarification of Inspection To Determine Modification Level

    One commenter, a private citizen, requests that we clarify the 
proposed requirements of the original NPRM for inspecting to determine 
the modification level of the NRM. The commenter states that the 
proposed requirements of paragraph (k) of the original NPRM as 
currently written do not make sense. Paragraph (k) states: ``If the 
inspection to determine whether Mod L is installed, as required by 
paragraph (j) of this AD, is done within the compliance time specified 
in paragraph (f) of this AD, paragraph (f) of this AD does not need to 
be done.'' The commenter explains that, since paragraph (f) was 
required to be accomplished within 5 days after March 11, 2003, it 
would not be possible to comply with paragraph (j) within that same 
time frame, since March 16, 2003, has already gone by. The commenter 
also states that the requirement of paragraph (j) to inspect for the 
installation of modification L, N, P, or R, is contradicted by the 
opening clause of paragraph (k), and asserts that this can't be the 
intent of paragraph (k) in the original NPRM. The commenter suggests 
that, to clear up this confusion and make it possible to accomplish the 
requirements of the related paragraphs, paragraph (k) should be 
reworded as follows: ``If the inspection to determine whether Mod L is 
installed, as required by paragraph (g) of this AD, is done within the 
compliance time specified in paragraph (f) of this AD, paragraph (j) of 
this AD does not need to be done.''
    We do not agree with this request. We have determined that the 
wording of paragraph (k) of the original NPRM reflects the correct 
compliance time for both paragraphs (f) and (g) of the original NPRM. 
Further, paragraph (j) is required regardless of compliance time or the 
findings of paragraph (f). Therefore, we have not changed paragraph (k) 
in this supplemental NPRM.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    The changes discussed above expand the scope of the original NPRM; 
therefore, we have determined that it is necessary to reopen the 
comment period to provide additional opportunity for public comment on 
this supplemental NPRM. This proposed AD would supersede AD 2003-04-06. 
This proposed AD would retain the requirements of the existing AD. This 
proposed AD would also require accomplishing the actions specified in 
the service information described previously, except as discussed under 
``Differences Between the Proposed AD and Service Information.''

Differences Between the Proposed AD and Service Information

    The service information specifies reporting certain information and 
returning parts to the manufacturer. However, this proposed AD would 
not require those actions.

Explanation of Changes Made to This Proposed Supplemental NPRM

    We have revised this supplemental NPRM to clarify the appropriate 
procedure for notifying the principal inspector before using any 
approved AMOC on any airplane to which the AMOC applies.
    After the original NPRM was issued, we reviewed the figures we have 
used over the past several years to calculate AD costs to operators. To 
account for various inflationary costs in the airline industry, we find 
it necessary to increase the labor rate used in these calculations from 
$65 per work hour to $80 per work hour. The cost impact information, 
below, reflects this increase in the specified hourly labor rate.

Costs of Compliance

    For the purposes of this proposed AD, we estimate that there are 
3,063 aircraft worldwide that may be equipped with a part that is 
subject to this proposed AD, including about 1,500 aircraft of U.S. 
registry.
    The inspection to determine whether Mod L has been done, which is 
currently required by AD 2003-04-06 and retained in this proposed AD, 
takes about 1 work hour per aircraft, at an average labor rate of $80 
per work hour. Based on these figures, the estimated cost of the 
currently required actions is $80 per aircraft.

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 supplemental NPRM 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 28830]]

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing amendment 39-13054 (68 FR 
8539, February 24, 2003) and adding the following new airworthiness 
directive (AD):

Various Aircraft: Docket No. FAA-2005-20080; Directorate Identifier 
2003-NM-193-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by June 12, 
2006.

Affected ADs

    (b) This AD supersedes AD 2003-04-06.

Applicability

    (c) This AD applies to aircraft, certificated in any category, 
equipped with a Honeywell Primus II RNZ-850/-851 Integrated 
Navigation Unit (INU) having a part number identified in Table 1 of 
this AD; including, but not limited to, BAE Systems (Operations) 
Limited (Jetstream) Model 4101 airplanes; Bombardier BD-700-1A10 
series airplanes; Bombardier CL-215-6B11 (CL415 variant) series 
airplanes; Cessna Model 560, 560XL, and 650 airplanes; Dassault 
Model Mystere-Falcon 50 series airplanes; Dornier Model 328-100 and 
-300 series airplanes; Empresa Brasileira de Aeronautica S.A. 
(EMBRAER) Model EMB-135 and -145 series airplanes; Learjet Model 45 
airplanes; Raytheon Model Hawker 800XP and Hawker 1000 airplanes; 
and Sikorsky Model S-76A, S-76B, and S-76C aircraft.

                        Table 1.--INU Part Numbers
------------------------------------------------------------------------
                              Part numbers
-------------------------------------------------------------------------
7510100-811 through 7510100-814 inclusive.
7510100-831 through 7510100-834 inclusive.
7510100-901 through 7510100-904 inclusive.
7510100-911 through 7510100-914 inclusive.
7510100-921 through 7510100-924 inclusive.
7510100-931 through 7510100-934 inclusive.
------------------------------------------------------------------------


    Note 1: This AD applies to Honeywell Primus II RNZ-850/-851 INUs 
installed on any aircraft, regardless of whether the aircraft has 
been otherwise modified, altered, or repaired in the area subject to 
the requirements of this AD. For aircraft that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (m) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

Unsafe Condition

    (d) This AD results from reports indicating that erroneous 
glideslope indications have occurred on certain aircraft equipped 
with the subject INUs. We are issuing this AD to ensure that the 
flightcrew has an accurate glideslope deviation indication. An 
erroneous glideslope deviation indication could lead to the aircraft 
making an approach off the glideslope, which could result in impact 
with an obstacle or terrain.

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 2003-04-06

Compliance Time for Action

    (f) Within 5 days after March 11, 2003 (the effective date of AD 
2003-04-06, amendment 39-13054), accomplish the requirements of 
either paragraph (g) or (h) of this AD. After the effective date of 
this AD, only accomplishing the requirements of paragraph (g) of 
this AD is acceptable for compliance with this paragraph.

Inspection To Determine Part Number

    (g) Perform a one-time general visual inspection of the 
modification plate for the Honeywell Primus II NV-850 Navigation 
Receiver Module (NRM); part number 7510134-811, -831, -901, or -931; 
which is part of the Honeywell Primus II RNZ-850/-851 INU; to 
determine if Mod L has been installed. The modification plate is 
located on the bottom of the Honeywell Primus II RNZ-850/-851 INU, 
is labeled NV-850, and contains the part number and serial number 
for the Honeywell Primus II NV-850 NRM. If Mod L is installed, the 
letter L will be blacked out. Honeywell Service Bulletin 7510100-34-
A0035, dated July 11, 2003, is an acceptable source of service 
information for the inspection required by this paragraph.
    (1) If Mod L is installed, before further flight, do paragraph 
(h) or (j) of this AD. After the effective date of this AD, only 
accomplishment of paragraph (j) is acceptable for compliance with 
this paragraph.
    (2) If Mod L is not installed, no further action is required by 
this paragraph.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``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 enhance visual access to all exposed 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.''



    Note 3: For more information on the inspection specified in 
paragraph (g) of this AD, refer to Honeywell Technical Newsletter 
A23-3850-001, Revision 1, dated January 21, 2003.

Aircraft Flight Manual Revision

    (h) Revise the Limitations section of the aircraft flight manual 
(AFM) to include the following statements (which may be accomplished 
by inserting a copy of the AD into the AFM):

``FLIGHT LIMITATIONS''

    When crossing the Outer Marker on glideslope, the altitude must 
be verified with the value on the published procedure.
    For aircraft with a single operating glideslope receiver, the 
approach may be flown using normal procedures no lower than 
Localizer Only Minimum Descent Altitude (MDA).
    For aircraft with two operating glideslope receivers, the 
aircraft may be flown to the published minimums for the approach 
using normal procedures if both glideslope receivers are tuned to 
the approach and both crew members are monitoring the approach using 
independent data and displays.''

Parts Installation

    (i) As of March 11, 2003, no person may install a Honeywell 
Primus II NV-850 NRM on which Mod L has been installed, on the 
Honeywell Primus II RNZ-850/-851 INU of any aircraft, unless 
paragraph (h) or (k) of this AD is accomplished. As of the effective 
date of this AD, only accomplishment of paragraph (k) is acceptable 
for compliance with this paragraph.

New Requirements of This AD

Inspection To Determine Modification Level of NRM

    (j) For aircraft on which Mod L was found to be installed during 
the inspection required by paragraph (g) of this AD, or for aircraft 
on which paragraph (h) of this AD was accomplished: Within 24 months 
after the effective date of this AD, do an inspection of the 
modification plate on the Honeywell Primus II NV-850 NRM; part 
number 7510134-811, -831, -901, or -931; which is part of the 
Honeywell Primus II RNZ-850/-851 INU; to determine if Mod L, N, P, R 
or T is installed. The modification plate located on the bottom of 
the Honeywell Primus II RNZ-850/-851 INU is labeled NV-850, and 
contains the part number and serial number for the Honeywell Primus 
II NV-850 NRM. If Mod L, N, P, R or T is installed, the 
corresponding letter on the modification plate will be blacked out. 
Honeywell Service Bulletin 7510100-34-A0035, dated July 11, 2003, is 
an acceptable source of service information for this inspection. If 
Mod T is installed, no further action is required by this paragraph. 
If Mod L, N, P, or R is installed, before further flight, do all 
applicable related investigative, corrective, and other specified 
actions, in accordance with the Accomplishment Instructions of 
Honeywell Service Bulletin 7510100-34-A0035, dated

[[Page 28831]]

July 11, 2003; and Honeywell Service Bulletin 7510100-34-0037, dated 
July 8, 2004; to ensure that the NRM is at the Mod T configuration. 
Once the actions in this paragraph are completed, the AFM revision 
required by paragraph (h) of this AD may be removed from the AFM.

    Note 4: Honeywell Service Bulletin 7510100-34-A0035, dated July 
11, 2003, refers to Honeywell Service Bulletin 7510100-34-A0034, 
dated February 28, 2003, as an additional source of service 
information for inspecting to determine the NRM part number, marking 
the modification plates of the NRM and INU accordingly, testing the 
INU for discrepant signals, and replacing the unit with a new or 
modified INU, as applicable. Honeywell Service Bulletin 7510100-34-
A0034 refers to Honeywell Service Bulletin 7510134-34-A0016, 
currently at Revision 001, dated March 4, 2003, as an additional 
source of service information for marking the modification plates of 
the NRM and INU.



    Note 5: Honeywell Service Bulletin 7510100-34-0037, dated July 
8, 2004, refers to Honeywell Service Bulletin 7510134-34-0018, dated 
July 8, 2004, as an additional source of service information for 
modifying the NRM to the Mod T configuration.


    (k) If the inspection specified by paragraph (j) of this AD is 
done within the compliance time specified in paragraph (f) of this 
AD, paragraph (g) of this AD does not need to be done.

No Reporting Requirement

    (l) Where Honeywell Service Bulletin 7510100-34-A0035 (or any of 
the related service information referenced therein) specifies to 
submit certain information to the manufacturer, this AD does not 
include that requirement.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Los Angeles 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) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

    Issued in Renton, Washington, on May 9, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-7559 Filed 5-17-06; 8:45 am]
BILLING CODE 4910-13-P