AD Amdt-39-10480

[Federal Register Volume 63, Number 75 (Monday, April 20, 1998)]
[Rules and Regulations]
[Pages 19391-19393]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-10276]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-114-AD; Amendment 39-10480; AD 98-09-01]
RIN 2120-AA64


Airworthiness Directives; Gulfstream Model GV 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 GV series airplanes. This 
action requires inspections and functional tests of the elevator 
Hardover Prevention System (HOPS) to detect any miswiring of electrical 
connectors, correction of any discrepancy found, and eventual 
modification of the HOPS wiring. This amendment is prompted by reports 
of incorrect matching of electrical connectors to the hydraulic 
deactivation valves of the elevator HOPS. The actions specified in this 
AD are intended to prevent the incorrect operation of the elevator 
HOPS, which could result in loss of control of the airplane.

DATES: Effective May 5, 1998.
    The incorporation by reference of certain publications listed in 
the

[[Page 19392]]

regulations is approved by the Director of the Federal Register as of 
May 5, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before June 19, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-114-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    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, Small Airplane Directorate, 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: Neil Berryman, Aerospace Engineer, 
Systems and Flight Test Branch, ACE-116A, FAA, Small Airplane 
Directorate, Atlanta Aircraft Certification Office, One Crown Center, 
1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30337-2748; 
telephone (770) 703-6066; fax (770) 703-6097.

SUPPLEMENTARY INFORMATION: The FAA has received reports indicating 
that, during recent inspections and operational tests of the elevator 
Hardover Prevention System (HOPS) on certain Gulfstream Model GV series 
airplanes, a configuration discrepancy was identified in which certain 
electrical connectors were incorrectly connected to the hydraulic 
deactivation valves of the elevator HOPS. The flight control hydraulic 
servos on the Gulfstream Model GV series airplane incorporate two 
redundant actuator pistons. The HOPS is designed to detect a runaway 
(or hardover) condition in either of these actuator pistons, and to 
subsequently shut down the affected side of the hydraulic servo. If the 
elevator HOPS is wired incorrectly, the system will shut down the wrong 
side of the hydraulic servo although that actuator is still operating 
properly. This condition, if not corrected, would prevent the correct 
operation of the elevator HOPS, which could result in loss of control 
of the airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Gulfstream Aerospace Alert 
Customer Bulletin No. 3, dated February 25, 1998, which describes 
procedures for performing a one-time inspection of the elevator HOPS to 
detect any incorrect wiring connections associated with the HOPS 
hydraulic deactivation valves, and corrective action, if necessary. The 
alert customer bulletin also describes procedures for a one-time 
functional test to ensure correct operation of the elevator HOPS.
    In addition, the FAA has reviewed and approved Gulfstream Aerospace 
GV Customer Bulletin No. 4, dated March 31, 1998, which describes 
procedures for modifying the electrical harness of the hydraulic 
deactivation valves of the left elevator HOPS, and installing 
additional identification decals in order to prevent future miswiring. 
Accomplishment of the actions specified in this customer bulletin 
eliminates the need for the inspection and functional test specified in 
Gulfstream Alert Customer Bulletin No. 3.

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 the incorrect operation of the elevator HOPS, 
which could result in loss of control of the airplane. This AD requires 
accomplishment of the actions specified in the customer bulletins 
described previously, except as discussed below.

Differences Between This Rule and Customer Bulletin

    Operators should note that Gulfstream Aerospace Alert Customer 
Bulletin No. 3, dated February 25, 1998, describes a one-time 
inspection and functional test to verify proper electrical 
configuration and operation of the elevator HOPS. The FAA has 
determined that, because of the safety implications and consequences 
associated with energizing the incorrect hydraulic deactivation valve 
of the elevator HOPS, performance of the inspection and functional test 
is necessary following accomplishment of any maintenance action 
associated with the elevator HOPS, until the wiring modifications 
described in Gulfstream Aerospace GV Customer Bulletin No. 4, dated 
March 31, 1998, are accomplished.
    Operators also should note that, although Gulfstream Aerospace 
Alert Customer Bulletin No. 3 specifies that the manufacturer may be 
contacted if technical assistance is required during accomplishment of 
the functional test, this AD requires that repair of any discrepancies 
be accomplished in accordance with a method approved by the FAA.

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.
    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 98-NM-114-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects on the States, on the relationship between the

[[Page 19393]]

national government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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:

98-09-01  Gulfstream Aerospace Corporation: Amendment 39-10480. 
Docket 98-NM-114-AD.

    Applicability: Model GV series airplanes, serial numbers 501 and 
504 through 540 inclusive, certificated in any category.

    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 the incorrect operation of the elevator Hardover 
Prevention System (HOPS), which could result in loss of control of 
the airplane, accomplish the following:
    (a) Within 25 flight hours after the effective date of this AD, 
accomplish the requirements of paragraphs (a)(1) and (a)(2) of this 
AD, in accordance with Gulfstream Aerospace Alert Customer Bulletin 
No. 3, dated February 25, 1998.
    (1) Perform a visual inspection to verify correct wire 
connections to the forward and aft hydraulic deactivation valve, 
left- and right-hand sides, of the elevator HOPS. If any connector 
is connected improperly, prior to further flight, re-connect the 
wiring in accordance with the alert customer bulletin. And
    (2) Perform a functional test to ensure correct operation of the 
elevator HOPS. If any discrepancy is found, prior to further flight, 
repair in accordance with a method approved by the Manager, Atlanta 
Aircraft Certification Office (ACO), FAA, Small Airplane 
Directorate.
    (b) Thereafter, repeat the actions required by paragraph (a) of 
this AD immediately following accomplishment of any maintenance 
actions on the elevator HOPS, until the actions required by 
paragraph (c) of the AD have been accomplished.
    (c) Within 150 flight hours after the effective date of this AD, 
modify the electrical harness of the hydraulic deactivation valves 
of the left elevator HOPS, and install additional identification 
decals, in accordance with Gulfstream Aerospace GV Customer Bulletin 
No. 4, dated March 31, 1998. Accomplishment of the requirements of 
this paragraph constitutes terminating action for this AD.
    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Atlanta ACO. 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

    (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.
    (f) The inspection and functional test shall be done in 
accordance with Gulfstream Aerospace Alert Customer Bulletin No. 3, 
dated February 25, 1998. The modification shall be done in 
accordance with Gulfstream Aerospace GV Customer Bulletin No. 4, 
dated March 31, 1998. 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; or at the 
FAA, Small Airplane Directorate, 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.
    (g) This amendment becomes effective on May 5, 1998.

    Issued in Renton, Washington, on April 13, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-10276 Filed 4-17-98; 8:45 am]
BILLING CODE 4910-13-U