[Federal Register Volume 62, Number 148 (Friday, August 1, 1997)]
[Rules and Regulations]
[Pages 41255-41257]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-20129]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-18-AD; Amendment 39-10096; AD 97-16-05]
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 all Gulfstream Model G-159 (G-I) airplanes, that
currently requires repetitive inspections to detect corrosion in the
wing planks under the bottom wing center fairings, and repair, if
necessary. This amendment requires the installation of a protective
paint system which, when accomplished, will allow the inspections to be
conducted at longer intervals. This amendment is
[[Page 41256]]
prompted by the development of a modification that will improve the
corrosion resistance of the subject area. The actions specified by this
AD are intended to detect and prevent corrosion in the lower skins of
the wing center section. If corrosion in this area remains unchecked,
it could reduce the integrity of the wing-to-fuselage fitting, and
consequently could lead to separation of the wing from the airplane.
DATES: Effective September 5, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 5, 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 67-04-01,
amendment 39-1234 (36 FR 12688, July 3, 1971), which is applicable to
all Gulfstream Model G-159 (G-I) airplanes, was published in the
Federal Register on March 6, 1997 (62 FR 10224). The action proposed to
continue to require the repetitive visual inspections, specified in AD
67-04-01, to detect corrosion of the wing planks under the bottom wing
center fairing assemblies, and repair, if necessary.
For airplanes on which a protective paint system had not been
installed previously, the action proposed to require that the
inspection continue to be repeated at intervals of 6 months (26 weeks),
until a protective paint system is installed within 12 months. Once the
paint system is installed, the repetitive inspections were proposed to
be required to continue, but the repetitive interval would be extended
to 18 months.
For airplanes on which a protective paint system was installed
previously, the action proposed to extend the currently-required
repetitive inspection interval of 12 months to 18 months.
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 67-04-01, and
those that are required by this action, take approximately 40 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 required
inspection actions on U.S. operators is estimated to be $172,800, or
$2,400 per airplane, per inspection.
The installation of the protective paint system that is required by
this AD action will take approximately 30 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Required
materials will cost approximately $100 per airplane. Based on these
figures, the cost impact of this requirement of this AD on U.S.
operators is estimated to be $136,800, or $1,900 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 39-1234 (36 FR
12688, July 3, 1971), and by adding a new airworthiness directive (AD),
amendment 39-10096, to read as follows:
97-16-05 Gulfstream Aerospace Corporation: Amendment 39-10096.
Docket 97-NM-18-AD. Supersedes AD 67-04-01, Amendment 39-1234.
Applicability: All Model G-159 (G-I) airplanes, certificated in
any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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 41257]]
To detect and prevent corrosion in the lower skins of the wing
center section, which could reduce the integrity of the wing-to-
fuselage fitting and consequently could lead to separation of the
wing from the airplane, accomplish the following:
(a) For all airplanes: Within 4 weeks after July 3, 1971 (the
effective date of AD 67-04-01, amendment 39-1234), remove the bottom
wing center fairings having part numbers (P/N) 159W10400-121 and
159W10401-121, or use an FAA-approved equivalent method, to perform
a visual inspection to detect corrosion of the wing planks under
these fairings.
Note 2: Paragraph (a) of this AD merely restates the actions
previously required by AD 67-04-01, amendment 39-1234. As allowed by
the phrase, ``unless accomplished previously,'' if those
requirements of AD 67-04-01 have already been accomplished, this AD
does not require that those actions be repeated.
Note 3: Care must be exercised when removing the fairings, since
the attaching rivets go into the pressure vessel. Use caution not to
enlarge rivet holes when removing rivets. When reinstalling the
fairings, an adequate type fastener and sealant must be used.
Note 4: Grumman Service Newsletter, Volume 166, dated August-
September 1966, pertains to this subject.
(b) For airplanes on which a protective paint system has not
been installed in accordance with Grumman Gulfstream I Aircraft
Service Change No. 190, dated June 28, 1971: Accomplish paragraphs
(b)(1) and (b)(2) of this AD. As of the effective date of this AD,
the inspections required by this paragraph shall be accomplished in
accordance with Grumman Gulfstream I Aircraft Service Change No.
190, dated June 28, 1971.
Note 5: The repeated inspection referred to in this paragraph is
the same inspection previously required by AD 67-04-01. Paragraph
(b)(1) of this AD merely restates the requirement of AD 67-04-01 to
repeat the inspection at intervals of 6 months. Paragraph (b)(2)
permits the reinspection interval to be extended to 18 months once
the specified protective paint system is installed.
(1) As a result of the inspection required by paragraph (a) of
this AD:
(i) If no corrosion is detected, repeat the inspection
thereafter at intervals not to exceed 6 months (26 weeks) until the
actions specified in paragraph (b)(2) of this AD are accomplished.
(ii) If any corrosion is detected, prior to further flight,
either repair the corroded part with an FAA-approved repair; or
replace the corroded part with a new or serviceable part of the same
part number; or replace the corroded part with a part approved by
the FAA. Thereafter, continue to perform the inspection at intervals
not to exceed 6 months (26 weeks) until paragraph (b)(2) of this AD
is accomplished.
(2) Within 12 months after the effective date of this AD,
install the protective paint system in accordance with Grumman
Gulfstream I Aircraft Service Change No. 190, dated June 28, 1971.
After installation, continue to perform the inspection required by
this paragraph at intervals not to exceed 18 months.
(c) For airplanes on which a protective paint system has been
installed previously in accordance with Grumman Gulfstream I
Aircraft Service Change
No. 190, dated June 28, 1971: Accomplish paragraphs (c)(1) and
(c)(2) of this AD. As of the effective date of this AD, the
inspections required by this paragraph shall be accomplished in
accordance with Grumman Gulfstream I Aircraft Service Change No.
190, dated June 28, 1971.
Note 6: The repeated inspection referred to in this paragraph is
the same inspection previously required by AD 67-04-01. Paragraph
(c)(1) of this AD merely restates the requirement of AD 67-04-01 to
repeat the inspection at intervals of 12 months. Paragraph (c)(2)
permits the reinspection interval to be extended to 18 months.
(1) As a result of the inspection required by paragraph (a) of
this AD:
(i) If no corrosion is detected, repeat the inspection
thereafter at intervals not to exceed 12 months until paragraph
(c)(2) of this AD is accomplished.
(ii) If any corrosion is detected, prior to further flight,
either repair the corroded part with an FAA-approved repair; or
replace the corroded part with a new or serviceable part of the same
part number; or replace the corroded part with a part approved by
the FAA. Thereafter, continue to perform the inspection at intervals
not to exceed 12 months until paragraph (c)(2) of this AD is
accomplished.
(2) Within 18 months since the last inspection accomplished in
accordance with paragraph (c)(1) of this AD (i.e., the last
inspection accomplished in accordance with AD 67-04-01), repeat the
inspection specified in paragraph (c)(1) of this AD.
(i) If no corrosion is detected, repeat the inspection
thereafter at intervals not to exceed 18 months.
(ii) If any corrosion is detected, prior to further flight,
repair in accordance with the service change. After repair, continue
to perform the inspection at intervals not to exceed 18 months.
(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 67-04-01, amendment 39-1234, are approved as
alternative methods of compliance with this AD.
Note 7: 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 I Aircraft
Service Change No. 190, dated June 28, 1971. 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 September 5, 1997.
Issued in Renton, Washington, on July 25, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-20129 Filed 7-31-97; 8:45 am]
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