[Federal Register Volume 62, Number 128 (Thursday, July 3, 1997)]
[Rules and Regulations]
[Pages 35957-35959]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-17283]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-16-AD; Amendment 39-10068; AD 97-14-10]
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 modification and repetitive
[[Page 35958]]
inspections for cracks in the main landing gear (MLG) retract cylinder
attachment fittings. This amendment requires installation of improved
attachment fittings which, when accomplished, terminates the
requirement for the repetitive inspections. 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 MLG retract cylinder attachment
fitting due to fatigue cracking. This condition, if not corrected,
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 67-31-08,
amendment 39-515 (32 FR 16201, November 28, 1967), which is applicable
to certain Gulfstream Model G-159 (G-I) airplanes, was published in the
Federal Register on March 6, 1997 (62 FR 10228). The action proposed to
supersede AD 67-31-08 to continue to require repetitive inspections and
modification of the MLG retract cylinder attachment fittings, and
replacement, if necessary. It also proposed to require that the
attachment fitting assemblies eventually be replaced with assemblies
made of steel. Once this replacement is accomplished, the previously
required modification and 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 (G-I) 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 actions that are currently required by AD 67-31-08 take
approximately 3 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 $12,960, or $180 per airplane, per inspection.
The replacement action that is required by this AD action will take
approximately 45 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will cost approximately
$5,400 per airplane. Based on these figures, the cost impact of the
requirements of this AD on U.S. operators is estimated to be $583,200,
or $8,100 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 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 39-515 (32 FR
16201, November 28, 1967), and by adding a new airworthiness directive
(AD), amendment 39-10068, to read as follows:
97-14-10 Gulfstream Aerospace Corporation (formerly Grumman):
Amendment 39-10068. Docket 97-NM-16-AD. Supersedes AD 67-31-08,
Amendment 39-515.
Applicability: Model G-159 (G-I) airplanes; serial numbers (S/N)
1 through 12 inclusive, 14 through 112 inclusive, 114 through 148
inclusive, 322, and 323; on which main landing gear cylinder attach
fitting assemblies having part number (P/N) 159WM10276-1 and -2 and
balls having P/N 159WM10277-1 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 (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.
[[Page 35959]]
To prevent failure of the main landing gear (MLG) retract
cylinder attachment fittings due to fatigue cracking, which could
result in the inability to retract the MLG, accomplish the
following:
(a) Accomplish the actions specified in paragraphs (a)(1) and
(a)(2) of this AD, at the times indicated in those paragraphs and in
accordance with Grumman Gulfstream Customer Bulletin No. 172, dated
September 6, 1963.
(1) Beginning November 7, 1967 (the effective date of AD 67-31-
08, amendment 39-515), and prior to each flight, conduct a visual
inspection to detect cracks in the MLG retract cylinder attachment
fittings on the lower surface of the right-hand and left-hand wings
in the vicinity of the aft end of the fitting.
(2) Within 25 hours time-in-service after November 7, 1967,
accomplish the actions specified in paragraphs (a)(2)(i) and
(a)(2)(ii) of this AD:
(i) Conduct a dye penetrant inspection, in conjunction with at
least a 10X magnifying glass, to detect cracks in the MLG retract
cylinder attachment fittings on the lower surface of the right-hand
and left-hand wings in the vicinity of the aft end of the fitting.
Repeat this inspection thereafter at intervals not to exceed 25
hours time-in-service. And
(ii) Modify the aft end edges of the fitting by rounding them
off to approximately 1/32'' radius.
(b) If any crack is found during an inspection required by
paragraph (a) of this AD, prior to further flight, accomplish either
paragraph (b)(1) or (b)(2) of this AD:
(1) Replace the cracked part with a part of the same part number
that has been modified and inspected in accordance with paragraph
(a) of this AD, in accordance with Grumman Gulfstream Customer
Bulletin No. 172, dated September 6, 1963. Thereafter, continue the
inspections required by paragraph (a) of this AD. Or
(2) Replace the fitting assembly with an assembly having part
number (P/N) 159WM10276-1 or -2, and balls having P/N 159WM10277-1.
After accomplishing this replacement, the repetitive inspections of
that fitting required by paragraph (a) of this AD may be terminated.
(c) Within 400 hours time-in-service after the effective date of
this AD, replace the MLG retract cylinder attachment fitting
assemblies with assemblies having part numbers (P/N) 159WM10276-1
and -2, and balls having P/N 159WM10277-1. This replacement
constitutes terminating action for the inspection requirements of
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 67-31-08, amendment 39-515, 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.
(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 Gulfstream
Customer Bulletin No. 172, dated September 6, 1963. 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.
(g) 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. 97-17283 Filed 7-2-97; 8:45 am]
BILLING CODE 4910-13-U