[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 [www.gpo.gov]
[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
