[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]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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
