[Federal Register Volume 68, Number 176 (Thursday, September 11, 2003)]
[Rules and Regulations]
[Pages 53499-53501]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-22991]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-190-AD; Amendment 39-13302; AD 2003-18-11]
RIN 2120-AA64


Airworthiness Directives; Gulfstream Model G-V Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Gulfstream Model G-V series airplanes. This 
action requires a one-time inspection of the balance weight 
installation of the left and right ailerons for correctly installed 
attachment components, and corrective action if necessary. This action 
is necessary to prevent separation of the balance weights of the 
aileron, which could result in jamming of the pilot's aileron control 
system, subsequent loss of aileron control, and consequent reduced 
controllability of the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Effective September 26, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 26, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before November 10, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-190-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2003-NM-190-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 or 2000 or 
ASCII text.
    The service information referenced in this AD may be obtained from 
Gulfstream Aerospace Corporation, PO Box 2206, M/S D-10, Savannah, 
Georgia 31402-9980. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Atlanta Aircraft Certification Office, One 
Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia; or 
at the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Darby Mirocha, Aerospace Engineer, 
ACE-116A, FAA, Atlanta Aircraft Certification Office, One Crown Center, 
1895 Phoenix Boulevard, suite 450,

[[Page 53500]]

Atlanta, Georgia 30349; telephone (770) 703-6095; fax (770) 703-6097.

SUPPLEMENTARY INFORMATION: The FAA has received a report on a 
Gulfstream Model G-V series airplane of loss of aileron control 
authority on final approach during landing. Investigation revealed that 
the outboard balance weight of the left aileron had detached and was 
wedged between the aileron and the rear beam of the wing. Further 
investigation revealed that the attachment hardware (all nine fastener 
assemblies) for the balance weight was missing. Supporting data show 
that all the attachment hardware was not properly installed during 
assembly. Separation of the balance weights of the aileron could result 
in jamming of the pilot's aileron control system, subsequent loss of 
aileron control, and consequent reduced controllability of the 
airplane.

Explanation of Relevant Service Information

    We have reviewed and approved Gulfstream GV Customer Bulletin 104, 
dated June 9, 2003 (hereafter referred to as ``the service bulletin''), 
which describes procedures for a one-time inspection of the balance 
weight installation of the left and right ailerons for correctly 
installed attachment components, and corrective action if necessary. 
The corrective action includes ensuring proper engagement of the self-
locking nut by verifying that one to three threads of the screw/bolt 
are protruding, replacing any missing fasteners, and re-torqueing any 
loose fasteners. Accomplishment of the actions specified above is 
intended to adequately address the identified unsafe condition. 
Although the Accomplishment Instructions of the service bulletin 
describe procedures for recording and reporting compliance with the 
service bulletin, this AD does not require those actions.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, this AD requires accomplishment of the actions 
specified in the service bulletin described previously, except as 
discussed below.

Difference Between This AD and the Service Bulletin

    The service bulletin refers only to an ``inspection'' of the 
balance weight installation of the left and right ailerons for 
correctly installed attachment components. We have determined that the 
procedures in the service bulletin should be described as a ``general 
visual inspection.'' Note 1 has been included in this AD to define this 
type of inspection.

Changes to 14 CFR Part 39/Effect on the AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance (AMOCs). Because we have now included this material in part 
39, only the office authorized to approve AMOCs is identified in each 
individual AD.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the AD is 
being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2003-NM-190-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

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.

[[Page 53501]]

Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-18-11 Gulfstream Aerospace Corporation: Amendment 39-13302. 
Docket 2003-NM-190-AD.

    Applicability: Model G-V series airplanes, serial numbers 501 
through 667 inclusive, and serial number 699; certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent separation of the balance weights of the aileron, 
which could result in jamming of the pilot's aileron control system, 
subsequent loss of aileron control and consequent reduced 
controllability of the airplane, accomplish the following:

One-Time Inspection/Corrective Action if Necessary

    (a) Within the next 50 landings or 90 days after the effective 
date of this AD, whichever is first: Do a one-time general visual 
inspection of the balance weight installation of the left and right 
ailerons for correctly installed attachment components (including 
any corrective actions) by doing all the actions specified in 
paragraphs II.A. through G. of the Accomplishment Instructions of 
Gulfstream GV Customer Bulletin 104, dated June 9, 2003. Do the 
actions per the service bulletin. Any applicable corrective actions 
must be done before further flight.

    Note 1: 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.''

Alternative Methods of Compliance

    (b) In accordance with 14 CFR 39.19, the Manager, Atlanta 
Aircraft Certification Office (ACO), FAA, is authorized to approve 
alternative methods of compliance for this AD.

Incorporation by Reference

    (c) The actions shall be done in accordance with Gulfstream GV 
Customer Bulletin 104, dated June 9, 2003. This incorporation by 
reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from Gulfstream Aerospace Corporation, PO Box 2206, M/S D-
10, Savannah, Georgia 31402-9980. Copies may be inspected at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Atlanta Aircraft Certification Office, 
One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, 
Georgia; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

Effective Date

    (d) This amendment becomes effective on September 26, 2003.

    Issued in Renton, Washington, on September 4, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-22991 Filed 9-10-03; 8:45 am]
BILLING CODE 4910-13-P