Airworthiness Directives; Gulfstream Aerospace Corporation Model G-159 (G-I) Airplanes

[Federal Register Volume 62, Number 128 (Thursday, July 3, 1997)]
[Rules and Regulations]
[Pages 35950-35951]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-17279]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-17-AD; Amendment 39-10066, AD 97-14-08]
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 cracks and 
loose rivets in the forward brackets for the main landing gear (MLG) 
uplock beam assembly, and replacement of the brackets, if necessary. 
This amendment requires installation of redesigned brackets that 
preclude the potential for cracking and loose rivets, when 
accomplished, this installation constitutes terminating action for the 
currently required inspections. This amendment is prompted by the 
development of an installation that will positively address the 
identified unsafe condition. The actions specified by this AD are 
intended to prevent failure of the bracket for the MLG uplock beam 
assembly due to cracking and loose rivets; such failure could result in 
the inability to retract the MLG.

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 66-10-03, 
amendment 39-222 (31 FR 5660, April 12, 1966), which is applicable to 
certain Gulfstream Model G-159 (G-I) airplanes, was published in the 
Federal Register on March 6, 1997 (62 FR 10237). The action proposed to 
require repetitive dye penetrant and visual inspections to detect 
cracks and loose rivets in the forward brackets of the main landing 
gear (MLG) uplock beam assembly, and replacement of the brackets, if 
necessary. It also proposed to require that the currently-installed 
brackets be replaced with improved brackets. Once this replacement is 
accomplished, the previously required inspections may be terminated.
    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 AD.
    The inspections that are currently required by AD 66-10-03 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 terminating replacement 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 $425 per airplane. Based on these figures, the cost 
impact of the requirements of this AD on U.S. operators is estimated to 
be $82,440, or $1,145 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.

Regulatory Impact

    The regulation 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 his 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 39-222 (31 FR 
5660, April 12, 1966), and by adding a

[[Page 35951]]

new airworthiness directive (AD), amendment 39-10066, to read as 
follows:

97-14-08 Gulfstream Aerospace Corporation (formerly Grumman): 
Amendment 39-10066. Docket 97-NM-17-AD. Supersedes AD 66-10-03, 
Amendment 39-222.

    Applicability: Model G-159 (G-I) airplanes; serial number (S/N) 
1 through 12 inclusive, 14 through 83 inclusive, and 114; on which 
main landing gear (MLG) uplock beam support brackets (angles) having 
part numbers (P/N) 159W10150-71 and -72 are not installed; 
confiscated 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)(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 brackets for the main landing gear 
(MLG) uplock beam assembly due to cracking and loose rivets, which 
could result in the inability to retract the MLG, accomplish the 
following:
    (a) Within 50 hours time-in-service after April 12, 1966 (the 
effective date of AD 66-10-03, amendment 39-222), and thereafter at 
intervals not to exceed 100 hours time-in-service, accomplish the 
actions specified in paragraphs (a)(1) and (a)(2) of this AD in 
accordance with Grumman Gulfstream Service Change No. 179, dated 
March 15, 1966:
    (1) Conduct a dye penetrant inspection, in conjunction with at 
least a 10X magnifying glass, to detect cracks in the MLG uplock 
beam forward brackets, P/N's 159W10150-51 and -52; and
    (2) Conduct a visual inspection of the attachments of each 
bracket to the firewall bulkhead and to the main gear uplock beam 
for loose rivets caused by elongated rivet holes.
    (b) If any crack or loose rivet is found during any inspection 
required by paragraph (a) of this AD, prior to further flight, 
accomplish either paragraph (b)(1) or (b)(2) of this AD, in 
accordance with Grumman Gulfstream Service Change No. 179, dated 
March 15, 1966:

    Note 2: Grumman Gulfstream Service Change No. 179A, dated March 
20, 1966, contains additional procedural information relevant to the 
inspection and replacement requirements of this AD.

    (1) Replace the bracket with a new or serviceable bracket having 
P/N 159W10150-51 or -52, as applicable. After this replacement, 
continue to inspect in accordance with paragraph (a) of this AD. Or
    (2) Replace the bracket with a bracket having P/N 159W10150-71 
or -72, as applicable. This replacement constitutes terminating 
action for the inspection required by paragraph (a) of this AD for 
the replaced bracket.
    (c) Within 1,000 hours time-in-service after the effective date 
of this AD, replace the brackets for the main landing gear (MLG) 
uplock beam assembly with brackets having P/N 159W10150-71 and -72, 
in accordance with Part II of Grumman Gulfstream Service Change No. 
179, dated March 15, 1966. Such replacement constitutes terminating 
action for the inspections required by this AD.
    (d)(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 66-10-03, amendment 39-222, are approved as 
alternative methods of compliance with this AD.

    Note 3: 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 actions shall be done in accordance with Grumman 
Gulfstream Service Change No. 179, dated March 15, 1966. 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, MS 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.
    (g) This amendment becomes effective on August 7, 1977.

    Issued in Renton, Washington, on June 26, 1997.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-17279 Filed 7-2-97; 8:45 am]
BILLING CODE 4910-13-M

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