[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