[Federal Register Volume 62, Number 128 (Thursday, July 3, 1997)]
[Rules and Regulations]
[Pages 35956-35957]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-17282]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-15-AD; Amendment 39-10067; AD 97-14-09]
RIN 2120-AA64
Airworthiness Directives; Gulfstream Aerospace Corporation Model
G-159 (G-I) Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Gulfstream Model G-159 (G-I) airplanes,
that currently requires repetitive inspections to detect cracking in
the mounting lugs of the elevator trim tab actuators, and replacement,
if necessary. This amendment requires the installation of improved
elevator trim tab actuators that are not susceptible to the subject
cracking. This amendment is prompted by the development of a
modification that positively addresses the identified unsafe condition.
The actions specified by this AD are intended to prevent failure of the
mounting lugs on the elevator trim tab actuator due to cracking; such
failure could result in severe vibration during flight and/or reduction
or loss of elevator trim tab capability, which could lead to reduced
controllability of the airplane.
DATES: Effective August 7, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 7, 1997.
ADDRESSES: The service information referenced in this AD may be
obtained from Gulfstream Aerospace Corporation, Technical Operations
Department, P.O. Box 2206, M/S D-10, Savannah, Georgia 31402-2206. This
information may be examined at the Federal Aviation Administration
(FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue,
SW., Renton, Washington; or at the FAA, Atlanta Aircraft Certification
Office, Small Airplane Directorate, Campus Building, 1701 Columbia
Avenue, Suite 2-160, College Park, Georgia; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Christina Marsh, Aerospace Engineer,
Airframe and Propulsion Branch, ACE-117A, FAA, Atlanta Aircraft
Certification Office, Small Airplane Directorate, Campus Building, 1701
Columbia Avenue, Suite 2-160, College Park, Georgia 30337-2748;
telephone (404) 305-7362; fax (404) 305-7348.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 72-24-04,
amendment 39-1559 (37 FR 24419, November 17, 1972), which is applicable
to certain Gulfstream Model G-159 (G-I) airplanes, was published in the
Federal Register on March 6, 1997 (62 FR 10231). The action proposed to
continue to require repetitive dye penetrant inspections for cracks in
the elevator trim tab actuator mounting lugs, and replacement, if
necessary. It also proposed to require the installation of improved
elevator trim tab actuators, which would constitute terminating action
for the repetitive inspections.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
There are approximately 146 Gulfstream Model G-159 airplanes of the
affected design in the worldwide fleet. The FAA estimates that 72
airplanes of U.S. registry will be affected by this proposed AD.
The inspections that are currently required by AD 72-24-04 take
approximately 2 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact of the currently required actions on U.S. operators is estimated
to be $8,640, or $120 per airplane, per inspection.
The new installation that is required by this AD action will take
approximately 12 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will cost approximately
$4,900 per airplane. Based on these figures, the cost impact of the
required requirements of this AD on U.S. operators is estimated to be
$404,640, or $5,620 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the requirements of this
AD action, and that no operator would accomplish those actions in the
future if this AD were not adopted.
[[Page 35957]]
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects 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, 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.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it 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 removing amendment 39-1559 (37 FR
24419, November 17, 1972), and by adding a new airworthiness directive
(AD), amendment 39-10067, to read as follows:
97-14-09 Gulfstream Aerospace Corporation (previously Grumman):
Amendment 39-10067. Docket 97-NM-15-A Supersedes AD 72-24-04,
Amendment 39-1559.
Applicability: Model G-159 (G-I) airplanes, on which elevator
trim tab actuators having part number 159SCC100-11 are not
installed; 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 (e)(1)
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 failure of the elevator trim tab mounting lugs due to
cracking, which could result in severe vibration during flight and a
consequent reduction or loss of elevator trim tab capability,
accomplish the following:
(a) Within 10 hours time-in-service after November 24, 1972 (the
effective date of AD 72-24-04, amendment 39-1559), perform an
inspection to detect cracks in the mounting lugs of the elevator
trim tab actuators, having part number (P/N) 159SCC100-1 or -5; and
shim to correct any out-of-plane condition, in accordance with
Gulfstream Customer Bulletin No. 208A, dated November 18, 1971;
Amendment 1, dated January 18, 1972; Amendment 2, dated April 21,
1972; and Gulfstream Operational Summary 72-5B, dated August 1972.
(b) If no crack is found in any mounting lug during the
inspection required by paragraph (a) of this AD, repeat the
inspection at intervals not to exceed 200 hours time-in-service.
(c) If any crack is found in a mounting lug when conducting any
inspection required by paragraph (a) or (b) of this AD, prior to
further flight, replace the elevator trim tab actuator with a new or
serviceable actuator having P/N 159SCC100-1, -5, or -11.
(1) If an actuator having P/N 159SCC100-1 or -5 is used as the
replacement unit, repeat the inspection for cracks specified in
paragraph (a) of this AD thereafter at intervals not to exceed 200
hours time-in-service.
(2) If an actuator having P/N 159SCC100-11 is used as the
replacement unit, no further inspection action is required for that
unit in accordance with this AD.
(d) Within 1,000 hours time-in-service after the effective date
of this AD, replace the elevator trim tab actuators with actuators
that have P/N 159SCC100-11, in accordance with Gulfstream Aircraft
Service Change No. 191, dated August 18, 1972. This installation
constitutes terminating action for the inspections required by this
AD.
(e)(1) 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 Aircraft Certification
Office (ACO), FAA, Small Airplane Directorate. 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.
(2) Alternative methods of compliance, approved previously in
accordance with AD 72-24-02, amendment 39-1559, are approved as
alternative methods of compliance with this AD.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(f) Special flight permits may be issued in accordance with
Secs. 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.
(g) The actions shall be done in accordance with Gulfstream
Customer Bulletin No. 208A, dated November 18, 1971; Gulfstream
Customer Bulletin No. 208A, Amendment 1, dated January 18, 1972;
Gulfstream Customer Bulletin No. 208A, Amendment 2, dated April 21,
1972; Gulfstream Operational Summary 72-5B, dated August 1972; or
Gulfstream Aircraft Service Change No. 191, dated August 18, 1972.
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,
Technical Operations Department, P.O. Box 2206, M/S D-10, Savannah,
Georgia 31402-2206. Copies may be inspected at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or
at the FAA, Atlanta Aircraft Certification Office, Small Airplane
Directorate, Campus Building, 1701 Columbia Avenue, Suite 2-160,
College Park, Georgia; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
(h) This amendment becomes effective on August 7, 1997.
Issued in Renton, Washington, on June 26, 1997.
S. R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-17282 Filed 7-2-97; 8:45 am]
BILLING CODE 4910-13-U
