[Federal Register Volume 62, Number 44 (Thursday, March 6, 1997)]
[Proposed Rules]
[Pages 10224-10226]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-5463]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 62, No. 44 / Thursday, March 6, 1997 /
Proposed Rules
[[Page 10224]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-18-AD]
RIN 2120-AA64
Airworthiness Directives; Gulfstream Aerospace Corporation Model
G-159 (G-I) Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of 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 action would require the
installation of a protective paint system which, when accomplished,
will allow the inspections to be conducted at longer intervals. This
action was prompted by the development of a modification that will
improve the corrosion resistance of the subject area. The actions
specified by the proposed 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: Comments must be received by April 14, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 97-NM-18-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056. Comments may be inspected at this location
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal
holidays.
The service information referenced in the proposed rule 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 FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Christina Marsh, Aerospace Engineer,
Airframe and Propulsion Branch, ACE-117A, FAA, Small Airplane
Directorate, Atlanta Aircraft Certification Office, Campus Building,
1701 Columbia Avenue, Suite 2-160, College Park, Georgia 30337-2748;
telephone (404) 305-7362; fax (404) 305-7348.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-NM-18-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 97-NM-18-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
In 1967, the FAA issued AD 67-04-01, amendment 39-1234 (36 FR
12688, July 3, 1971), applicable to all Gulfstream Model G-159 (G-I)
airplanes. That AD requires a visual inspection to detect corrosion of
the wing planks under the bottom wing center fairing assemblies (having
part numbers 159W10400-121 and 159W10401-121), and repair if necessary.
After the initial inspection is accomplished, and after any repair is
made, the inspection is required to be repeated at intervals of 26
weeks.
That action was prompted by reports indicating that corrosion was
found in the lower skins of the wing center section of several of these
airplanes. The requirements of that AD are intended to detect and
correct corrosion in this area. If such corrosion 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.
Actions Since Issuance of Previous Rule
As part of its on-going program to address issues relevant to the
continued operational safety of the aging transport fleet, the FAA,
along with Gulfstream Aerospace Corporation and several U.S. and non-
U.S. operators of the affected airplanes, agreed to undertake the task
of identifying and implementing procedures to ensure the continuing
structural airworthiness of aging commuter-class airplanes. This group
recently reviewed selected service bulletins, applicable to Gulfstream
Model G-159 airplanes, to be recommended for mandatory rulemaking
action to ensure the continued operational safety of these airplanes.
Explanation of Relevant Service Information
The group reviewed and recommended Grumman Gulfstream I Aircraft
Service Change No. 190, dated June 28, 1971, for mandatory regulatory
action. That service change describes procedures for repetitive
inspections to detect corrosion of the center section lower wing
planks, and repair, if necessary. It also describes the
[[Page 10225]]
installation of a protective paint system to the fairing assemblies and
bottom wing cover. This protective system is intended to improve the
corrosion resistance of this area. Once it is installed, the repetitive
inspections may be conducted at longer intervals.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would supersede AD 67-04-01. It would 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, this new action would 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 would 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, this new action would extend the currently-required
repetitive inspection interval of 12 months to 18 months.
These actions would be required to be accomplished in accordance
with the aircraft service change described previously.
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 would be affected by this proposed AD.
The inspections that are currently required by AD 67-04-01, and
those that would be required by this proposed 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 proposed 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 proposed in
this AD action would take approximately 30 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Required
materials would cost approximately $100 per airplane. Based on these
figures, the cost impact of the proposed requirements 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 current or proposed
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 proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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),
to read as follows:
Gulfstream Aerospace Corporation: 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.
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
[[Page 10226]]
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. Issued in Renton,
Washington, on February 27, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-5463 Filed 3-5-97; 8:45 am]
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