[Federal Register Volume 62, Number 140 (Tuesday, July 22, 1997)]
[Rules and Regulations]
[Pages 39101-39104]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-18497]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 62, No. 140 / Tuesday, July 22, 1997 / Rules
and Regulations
[[Page 39101]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 92-CE-41-AD; Amendment 39-10080; AD 97-08-06 R1]
RIN 2120-AA64
Airworthiness Directives; Louis L'Hotellier, S.A., Ball and
Swivel Joint Quick Connectors
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; correction.
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SUMMARY: This document clarifies information in Airworthiness Directive
(AD) 97-08-06 that applies to Louis L'Hotellier S.A. (L'Hotellier) ball
and swivel joint quick connectors installed on gliders and sailplanes
that are not equipped with a ``Uerling'' sleeve or an LS-safety sleeve.
These connectors allow the operator of the gliders and sailplanes to
quickly connect and disconnect the control systems during assembly and
disassembly for storage purposes. AD 97-08-06 currently requires
enlarging the safety pin guide hole diameter, and fabricating and
installing a placard that specifies the requirement of securing the
control system connectors with safety wire, pins, or safety sleeves
prior to each flight. The actions specified in that AD are intended to
prevent the connectors from becoming inadvertently disconnected, which
could result in loss of control of the sailplane or glider. This
document clarifies the applicability and modification instructions of
AD 97-08-06 by including additional instructions to accomplish the same
actions. This correction of the AD results from several operators
expressing uncertainty about the applicability and modification
instructions.
DATES: Effective August 1, 1997.
FOR FURTHER INFORMATION CONTACT: Mr. J. Mike Kiesov, Project Officer,
Sailplanes/Gliders, Small Airplane Directorate, Aircraft Certification
Service, FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64106;
telephone (816) 426-6932; facsimile (816) 426-2169.
SUPPLEMENTARY INFORMATION: On April 2, 1997, the Federal Aviation
Administration (FAA) issued AD 97-08-06, Amendment 39-9994 (62 FR
17537, April 10, 1997), which applies to gliders and sailplanes
utilizing the L'Hotellier ball and swivel joint quick connectors, and
that are not equipped with a ``Uerling'' sleeve or an LS-Safety sleeve.
That AD requires the following:
--Enlarging the safety pin guide hole diameter to a minimum of 1.2
mm (0.05 in.) to accommodate a safety wire or pin, as applicable.
--Fabricating a placard (using 1/8 inch letters) with the following
words:
``All L'Hotellier control system connectors must be secured with
safety wire, pins, or safety sleeves, as applicable, prior to
operation.''; and
--Installing this placard in the glider or sailplane within the
pilot's clear view.
The AD resulted from several in-flight accidents involving
inadvertent disconnection of these connectors that are installed on
certain gliders and sailplanes. The actions required by AD 97-08-06 are
intended to prevent the connectors from becoming inadvertently
disconnected, which could result in loss of control of the sailplane or
glider.
Need for the Correction
Since the issuance of AD 97-08-06, the FAA received several reports
from operators stating that they are not clear as to whether the AD
applies to their sailplane or glider.
The FAA also did not distinguish that there are two styles of ball
and swivel joint quick connectors (locking plates and locking cams),
which has led to confusion for affected sailplane and glider operators
in complying with the AD.
In addition, paragraph (a) of AD 97-08-06 requires the operator to
enlarge the safety pin guide hole of the quick connectors to accomodate
a safety wire or pin for those sailplanes or gliders equipped with the
affected quick connectors that have a safety pin guide hole. Paragraph
(b) of this AD requires fabricating and installing a placard that
specifies the requirement of securing the control system connectors
with safety wire, pins, or safety sleeves, as applicable, prior to each
flight. If a sailplane or glider is equipped with a quick connector
that does not have a safety pin guide hole, it would be impossible for
the owner /operator to comply with paragraph (b) of AD 97-08-06 without
drilling guide holes.
Consequently, the FAA saw a need to clarify the applicability of AD
97-08-06, to more fully explain the intent of the modification
requirements of AD 97-08-06, and to add the requirement of drilling
safety pin guide holes if not already equipped.
Correction of Publication
This document clarifies the applicability and modification
instructions of AD 97-08-06, and adds the AD as an amendment to section
39.13 of the Federal Aviation Regulations (14 CFR 39.13).
Since this action only clarifies the applicability and
modifications instructions, it has no adverse economic impact and
imposes no additional burden on any person than would have been
necessary to comply with paragraph (b) of AD 97-08-06. Therefore, the
FAA has determined that prior notice and opportunity for public comment
are unnecessary.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Correction
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 USC 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Airworthiness Directive
(AD) 97-07-10, Amendment 39-97-08-06, Amendment 39-9994 (62 FR 17537,
[[Page 39102]]
April 10, 1997), and by adding a new AD to read as follows:
97-08-06 R1 Louis L' Hotellier, S.A. Amendment 39-10080; Docket No.
92-CE-41-AD. Revises AD 97-08-06, Amendment 39-9994.
Applicability: All ball and swivel joint quick connectors
installed in, but not limited to, the following gliders and
sailplanes that are not equipped with a ``Uerling'' sleeve or an LS-
Safety sleeve:
------------------------------------------------------------------------
Manufacturer Models
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Alexander Schleicher...................... ASK21, ASK23, ASW 12, ASW15,
ASW15B, ASW17, ASW19,
ASW19B, S 12, AS-K13.
Centrair, S.N............................. 101, 101A, 101P, 101AP, and
201B.
Eiravion.................................. PIK 20, PIK 20B, and PIK
20D.
Glaser Dirks.............................. DG100, DG400, and DG-500M.
Burkhart Grob............................. G102 Astir CS, G102, G103
Twin Astir, G103 Twin II,
G103A Twin II Acro, G103C
Twin III SL, G109, and
G109B.
Intreprinderea ICA (Lark)................. IS-28B2 and IS-29D2.
Rolladen Schneider........................ LS1-f and LS3-a.
Schempp-Hirth............................. Cirrus, Std. Cirrus, Nimbus
2, Nimbus 2B, Janus, Discus
a, Ventus a/16.6.
------------------------------------------------------------------------
Note 1: This AD applies to the L'Hotellier ball and swivel joint
quick connectors. This AD only applies to U.S.type-certificated
gliders and sailplanes that have the affected connectors installed.
If the L'Hotellier connectors are not installed on a glider or
sailplane, no action is required by the owner/operator. This AD does
not apply to gliders and sailplanes that do not have a U.S. type
certificate (i.e., experimental category); however, the FAA strongly
recommends compliance with the intent of this AD for airplanes
involved in U.S. operation where a U.S. type certificate is not
necessary.
Note 2: This AD applies to sailplanes and gliders equipped with
the quick connectors identified in the preceding applicability
provision, regardless of whether sailplane or glider has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For sailplanes and gliders 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 (e) 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 within the next 30 calendar days after the
effective date of this AD or upon installation of the affected quick
connectors, whichever occurs later, unless already accomplished
(compliance with AD 97-08-06).
To prevent the quick connectors from becoming inadvertently
disconnected, which could result in loss of control of the sailplane
or glider, accomplish the following:
Note 3: The paragraph structure of this AD is as follows:
Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.
Level 4: (A), (B), (C), etc.
Level 2, Level 3, and Level 4 structures are designations of the
Level 1 paragraph they immediately follow.
(a) For all sailplanes and gliders equipped with the affected
quick connectors, accomplish the following:
(1) For ball and swivel joint connectors with lock plates,
accomplish the following:
(i) If the quick connectors have a safety pin guide hole,
utilize the existing hole and install an aviation locking device
(safety wire or safety pin). If the hole cannot accommodate the
locking device, enlarge the hole to a diameter not to exceed 1.2 mm
(0.05 inch), and install the locking device.
(A) If the locking device already fits the guide hole, then
enlarging the hole is not necessary.
(B) The type of aviation locking device used is at the
discretion of the certificated mechanic based on the installation
accessibility of the locking devices and fittings.
(ii) If the quick connectors do not have a safety pin guide
hole, drill a guide hole not to exceed 1.2 mm (0.05 inch) to
accommodate the aviation locking device and install the locking
device (Reference Figure 1). The type of aviation locking device
used is at the discretion of the certificated mechanic based on the
installation accessibility of the locking devices and fittings.
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[[Page 39103]]
[GRAPHIC] [TIFF OMITTED] TR22JY97.008
(2) For ball and swivel joint quick connectors with locking
cams, accomplish the following:
(i) If the locking cam does not have a safety pin guide hole,
drill the hole not to exceed 1.3 mm (0.055 inch) to accommodate the
aviation locking device and install the locking device.
(A) When drilling the hole, assure that the ball is correctly
inserted so that one edge of the hole is level with the main body of
the joint and at least 1.5mm (0.0625 inch) of material is left on
the other side.
(B) When the ball is seated correctly, the hole is located aft
of the centerline of the cam pivot point. (See the dashed line in
Figure 2 of this AD).
(C) The type of aviation locking device used is at the
discretion of the certificated mechanic based on the installation
accessibility of the locking devices and fittings.
(ii) If the locking cam has a safety pin guide hole, either
utilize the existing hole and install an aviation locking device or
enlarge the hole to a diameter not to exceed 1.3mm (0.055 inch) to
accommodate the appropriate aviation locking device and install the
locking device.
(A) When enlarging the hole, assure that the ball is correctly
inserted so that one edge of the hole is level with the main body of
the joint and at least 1.5mm (0.0625 inch) of material is left on
the other side. It is recommended to have the ball and swivel joint
connected when the hole is drilled.
[[Page 39104]]
[GRAPHIC] [TIFF OMITTED] TR22JY97.009
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(B) When the ball is seated correctly, the hole is located aft
of the centerline of the cam pivot point. (See the dashed line in
Figure 2 of this AD).
(C) The type of aviation locking device used is at the
discretion of the certificated mechanic based on the installation
accessibility of the locking devices and fittings.
Note 4: The applicable aircraft manufacturer has identified
suitable locking devices based on the aircraft's specific type
design features. The operator may contact the U.S. aircraft company
representative or manufacturer for any technical information related
to this matter.
Note 5: It is recommended, but not required by this AD, that the
owner/operator inspect these connectors per L'Hotellier's
``Instructions for the Maintenance L'Hotellier Ball and Swivel
Joints.'' This technical data may be obtained from your U.S.
sailplane dealer or from: L'Hotellier S.A., 93 Avenue Charles De
Gaulle, 92270 Bois Colombes, France.
(b) Fabricate and install a placard (using 1/8 inch letters) in
the glider or sailplane, within the pilot's clear view, with the
following words:
``All L'Hotellier control system connectors must be secured with
safety wire, pins, or safety sleeves, as applicable, prior to
operation.''
(c) Fabricating and installing the placard as required by
paragraph (b) of this AD may be performed by the owner/operator
holding at least a private pilot certificate as authorized by
section 43.7 of the Federal Aviation Regulations (14 CFR 43.7), and
must be entered into the sailplane's or glider's records showing
compliance with this AD in accordance with section 43.9 of the
Federal Aviation Regulations.
(d) 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.
(e) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Small Airplane Directorate, Aircraft
Certification Service, FAA, 1201 Walnut, suite 900, Kansas City,
Missouri 64106. The request shall be forwarded through an
appropriate FAA Maintenance Inspector, who may add comments and then
send it to the Manager, Small Airplane Directorate. Alternative
methods of compliance approved in accordance with AD 97-08-06 are
considered approved as alternative methods of compliance for this
AD.
Note 6: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Small Airplane Directorate.
(f) Copies of this AD may be inspected at the FAA, Central
Region, Office of the Assistant Chief Counsel, Room 1558, 601 E.
12th Street, Kansas City, Missouri.
(g) This amendment (39-10080) becomes effective on August 1,
1997.
Issued in Kansas City, Missouri, on July 9, 1997.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-18497 Filed 7-21-97; 8:45 am]
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