[Federal Register Volume 66, Number 80 (Wednesday, April 25, 2001)]
[Rules and Regulations]
[Pages 20734-20737]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-9876]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-83-AD; Amendment 39-12191; AD 2001-08-13]
RIN 2120-AA64


Airworthiness Directives; Gulfstream Model G-1159, G-1159A, G-
1159B, G-IV, and 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-1159, G-1159A, G-1159B, G-
IV, and G-V series airplanes. This action requires an inspection to 
determine if certain door control valves of the landing gear are 
installed, and modification of the valve, if necessary. This action is 
necessary to prevent loss of hydraulic system fluid due to failure of 
the door control valve of the landing gear, which could require the 
flight crew to use alternate gear extension procedures (landing gear 
blow down) for landing of all models. This action is intended to 
address the identified unsafe condition.

DATES: Effective May 10, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 10, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before June 25, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114,

[[Page 20735]]

Attention: Rules Docket No. 2001-NM-83-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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. 2001-NM-83-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 for Windows or 
ASCII text.
    The service information referenced in this AD may be obtained from 
Gulfstream Aerospace Corporation, P.O. 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: Frank Mokry, Aerospace Engineer, 
Systems and Flight Test Branch, ACE-116A, FAA, Atlanta Aircraft 
Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 
450, Atlanta, Georgia 30349; telephone (770) 703-6066; fax (770) 703-
6097.

SUPPLEMENTARY INFORMATION: The FAA has received reports indicating that 
in-flight failures of a certain door control valve of the landing gear 
(Gulfstream part number (P/N) 1159SCH231-33 with Eaton/Sterer P/N 
65940-1) have occurred on Gulfstream Model G-IV and G-V series 
airplanes. Investigation has revealed that the spool and sleeve 
assembly were ejected from the valve body, which resulted in complete 
loss of system hydraulic fluid. The investigation also revealed that 
the cause of the ejection was pressure buildup in the cavity of the 
body behind the spool and sleeve assembly. Although that control valve 
has been incorporated into the Gulfstream fleet of airplanes since the 
certification of the G-II model, it has undergone various design and 
dash number changes over the years. The control valve is used for 
extension and retraction operations for the nose landing gear and the 
left and right main landing gear.
    Such failure of the door control valves of the landing gear, if not 
corrected, could result in complete loss of the combined hydraulic 
system fluid on Models G-1159, G-1159A, G-1159B, and G-IV series 
airplanes, and loss of fluid in the left hydraulic system in Model G-V 
series airplanes. Loss of the hydraulic system fluid requires the 
flight crew to use the airplane alternate gear extension procedures 
(landing gear blow down) for landing on all models.

Similar Condition on Other Models

    Door control valves of the landing gear having P/N 1159SCH231-33 
with Eaton/Sterer P/N 65940-1 that are installed on Gulfstream Model G-
IV and G-V series airplanes may also be installed on Gulfstream Model 
G-1159, G-1159A, and G-1159B series airplanes. Therefore, all of these 
models may be subject to the same unsafe condition.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Gulfstream G-II Alert Customer 
Bulletin (ACB) No. 27 (for Model G-1159 and G-1159A series airplanes), 
G-III ACB No. 13 (for Model G-1159B series airplanes), G-IV ACB No. 27 
(for Model G-IV), and G-V ACB No. 12 (for Model G-V series airplanes); 
all dated March 20, 2001. These ACB's describe procedures for 
performing a general visual inspection to determine if any door control 
valves of the landing gear having part number P/N 1159SCH231-33 with 
Eaton/Sterer P/N 65940-1,-1 Rev. A, or -1 Rev. B, are installed that 
contain certain serial numbers. The ACB's also describe procedures for 
modifying the door control valves by installing a new improved set 
screw with a pressure relief hole in it, filling with Dow Corning RTV 
732 sealant, and labeling the valve as P/N 65940-1 Rev. C. 
Accomplishment of the actions specified in the ACB's is intended to 
adequately address the identified unsafe condition.

Additional Source of Service Information

    The Gulfstream ACB's also reference Eaton Aerospace Sterer 
Engineering Service Bulletin 65940-27-01, dated March 1, 2001, as an 
additional source of service information.

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, this AD is 
being issued to prevent loss of hydraulic system fluid due to failure 
of the door control valve of the landing gear, which could require the 
flight crew to use alternate gear extension procedures (landing gear 
blow down) for landing of all models. This AD requires accomplishment 
of the actions specified in the ACB's described previously, except as 
discussed below.

Difference Between AD and the ACB's

    Operator's should note that the ACB's do not provide procedures to 
perform a visual inspection to determine if the specified Gulfstream 
and Eaton/Sterer valve P/N's are installed. Therefore, this AD provides 
those procedures in order to clarify that the inspection for certain 
serial numbers of the valves, and modification of the control valves, 
need only be done on airplane models having certain Gulfstream and 
Eaton/Sterer valve P/N's. Additionally, we have clarified that the 
requirements of this AD are unnecessary for airplane models that may 
have previously accomplished the replacement of the landing gear 
control valves with valves having P/N 65940-1 Rev. C.

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:
     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.
     For each issue, state what specific change to the AD is 
being requested.

[[Page 20736]]

     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 2001-NM-83-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

    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

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

2001-08-13  Gulfstream Aerospace Corporation: Amendment 39-12191. 
Docket 2001-NM-83-AD.

    Applicability: Model G-1159, G-1159A, G-1159B, G-IV, and G-V 
series airplanes, as specified in the Gulfstream Alert Customer 
Bulletins listed in the following table; certificated in any 
category:

  Table--Gulfstream Airplane Models and Alert Customer Bulletin's (ACB)
------------------------------------------------------------------------
              Model                 ACB No.              Dated
------------------------------------------------------------------------
G-1159 and G-1159A (G-II/IIB)             27  March 20, 2001.
 series airplanes.
G-1159B (G-III) series airplanes.         13  March 20, 2001.
G-IV series airplanes............         27  March 20, 2001.
G-V series airplanes.............         12  March 20, 2001.
------------------------------------------------------------------------


    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes 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 (d) 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.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent loss of hydraulic system fluid due to failure of the 
door control valve of the landing gear, which could require the 
flight crew to use alternate gear extension procedures (landing gear 
blow down) for landing of all models; accomplish the following:

Inspection and Replacement of Valves

    (a) Within 15 landings or 30 days after the effective date of 
this AD, whichever occurs later: Perform a general visual inspection 
to determine if any landing gear door control valve having 
Gulfstream part number (P/N) 1159SCH231-33 with Eaton/Sterer P/N 
65940-1, -1 Rev. A, or -1 Rev. B, is installed.

    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 under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, 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 no valve has those P/N's, no further action is required 
by this paragraph.
    (2) If all valves found have P/N 1159SCH231-33 with Eaton/Sterer 
P/N 65940-1, Rev. C, no further action is required by this 
paragraph.
    (b) If any valve has a door control valve of the landing gear 
having Gulfstream P/N 1159SCH231-33 with Eaton/Sterer P/N 65940-1 
and a serial number as specified in paragraph (b)(1) or (b)(2) of 
this AD: Replace the set screw with a new set screw, fill with Dow 
Corning RTV 732 sealant, and label the valve as P/N 65940-1 Rev. C; 
in accordance with Gulfstream G-II ACB No. 27 (for Model G-1159 and 
G-1159A series airplanes), G-III ACB No. 13 (for Model G-1159B 
series airplanes), G-IV ACB No. 27 (for Model G-IV series 
airplanes), and G-V ACB No.12 (for Model G-V series airplanes); all 
dated March 20, 2001, as applicable; at the times specified in 
paragraph (b)(1) or (b)(2), as applicable.
    (1) For valves having serial number 1900 or higher: Within 5 
landings or 15 days after the effective date of this AD, whichever 
occurs later.
    (2) For valves having a serial number less than 1900: Within 50 
landings or 90 days after the effective date of this AD, whichever 
occurs later.

    Note 3: The Gulfstream ACB's specified in paragraphs (a) and (b) 
of this AD reference Eaton Aerospace Sterer Engineering Service 
Bulletin 65940-27-01, dated March 1, 2001, as an additional source 
of service information.

    (c) As of the effective date of this AD, no person shall install 
on any airplane a door control valve of the landing gear, Gulfstream 
P/N 1159SCH231-33 with Eaton/Sterer P/N 65940-1, unless that valve 
has been modified in accordance with paragraph (b) of this AD.

Alternative Methods of Compliance

    (d) An alternative method of compliance or adjustment of the 
compliance time that

[[Page 20737]]

provides an acceptable level of safety may be used if approved by 
the Manager, Atlanta Aircraft Certification Office (ACO), FAA. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Atlanta ACO.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (f) With the exception of the general visual inspection required 
by paragraph (a) of this AD, the actions shall be done in accordance 
with Gulfstream G-II Alert Customer Bulletin No. 27, dated March 20, 
2001; Gulfstream G-III Alert Customer Bulletin No. 13, dated March 
20, 2001; Gulfstream G-IV Alert Customer Bulletin No. 27, dated 
March 20, 2001; and Gulfstream G-V Alert Customer Bulletin No. 12, 
dated March 20, 2001. 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, P.O. 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; 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

    (g) This amendment becomes effective on May 10, 2001.

    Issued in Renton, Washington, on April 16, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-9876 Filed 4-24-01; 8:45 am]
BILLING CODE 4910-13-P