[Federal Register Volume 64, Number 237 (Friday, December 10, 1999)]
[Rules and Regulations]
[Pages 69185-69188]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-32083]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-33-AD; Amendment 39-11460; AD 98-25-10 R1]
RIN 2020-AA64
Airworthiness Directives; Aircraft Belts, Inc. Model CS, CT, FM,
FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH Seat
Restraint Systems
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment revises an existing airworthiness directive
(AD), applicable to Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL,
JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH seat restraint
systems installed on, but not limited to, Beech Aircraft Corp., Bell
Helicopter Textron, Inc., Cessna Aircraft Co., Dassault Aviation,
Eurocopter Deutschland, Eurocopter France, Gulfstream Aerospace,
Learjet Corp., Lockheed Aircraft Corp., and Piper Aircraft Corp.
aircraft, that currently requires inspecting to ensure the locking
mechanism is engaging properly and replacing the buckle-half of the
seat restraint system, if necessary. This amendment will allow an
owner/operator (pilot) to determine if the locking mechanism is
engaging properly and will require replacing the buckle-half of the
seat restraint system, if necessary. This amendment is prompted by a
determination made by the FAA that pilots may perform the one-time
check of the locking mechanism and that only affected seat restraint
systems manufactured between March 1997 and November 1998 must be
checked. The actions specified by this AD are intended to prevent
failure of the seat restraint system due to the buckle assembly locking
mechanism not engaging properly, which could result in the seat
restraint system failing to properly secure the occupant during
turbulence or landing.
EFFECTIVE DATE: January 14, 2000.
FOR FURTHER INFORMATION CONTACT: Rob Romero, Aerospace Engineer,
Airplane Certification Office, ASW-150, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137, telephone (817) 222-5102, fax (817) 222-5960.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by revising AD 98-25-10,
Amendment 39-10936 (63 FR 67775, December 9, 1998), which is applicable
to Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU,
MD, ME, MM, MN, NB, PM, PN, RG, and RH seat restraint systems, was
published in the Federal Register (64 FR 47715, September 1, 1999). The
action proposed to allow a pilot to determine if the seat restraint
system's locking mechanism is engaging properly and required replacing
the buckle-half of the seat restraint system, if necessary.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter states that the proposal should be withdrawn because
it serves no useful purpose and will only generate confusion. In lieu
of a withdrawal, the commenter requests that the effective date of the
existing AD be stated in the compliance provision and that a note be
included in the revision that indicates operators who previously
complied with the AD are not affected by the revision. The FAA does not
concur with the commenter's suggestions.
[[Page 69186]]
While the AD revision is not intended to create any additional
requirements, there are valid reasons for its issuance. This revision
allows pilots to perform the required visual check; further, it
establishes limits on the manufacture dates to which the AD is
applicable. As to inserting a note giving credit to those that have
already performed the requirements, that is unnecessary since the
compliance provision allows this credit when it states ``unless
accomplished previously.''
The commenter also states that the cost estimate given in the
proposal is incorrect as the affected operators have already
accomplished the inspection/replacement. Additionally, the commenter
states that it would be more accurate to include in the cost estimate
the paperwork costs that operators must generate to update their AD
records to reflect the revised amendment number. The FAA does not
concur because all operators may not have reached the 10 hours time-in-
service compliance time.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
The FAA estimates that 12,278 seat restraint systems of U.S.
registry will be affected by this AD, that it will take approximately
one-half work hour to accomplish the required actions, and that the
average labor rate is $60 per work hour. Required parts will cost
approximately $10 per buckle half. Based on these figures, the total
cost impact of the AD on U.S. operators is estimated to be $368,340.
The regulations adopted herein will not impose substantial direct
compliance costs on states or local governments or 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 13132, the FAA has not consulted with
States or local authorities prior to the publication of this rule.
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 FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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 39-10936 (63 FR
67775, December 9, 1998), and by adding a new airworthiness directive
(AD), Amendment 39-11460, to read as follows:
AD 98-25-10 R1 Aircraft Belts, Inc.: Amendment 39-11460. Docket No.
98-SW-33-AD. Revises AD 98-25-10, Amendment 39-10936.
Applicability: Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD,
ME, MM, MN, NB, PM, PN, RG, and RH seat restraint systems
manufactured between March 1997 and November 1998 that are installed
on, but not limited to, Beech Aircraft Corp., Bell Helicopter
Textron, Inc., Cessna Aircraft Co., Dassault Aviation, Eurocopter
Deutschland, Eurocopter France, Gulfstream Aerospace, Learjet Corp.,
Lockheed Aircraft Corp., and Piper Aircraft Corp. aircraft,
certificated in any category.
Note 1: This AD applies to each seat restraint system 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 seat restraint systems
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) 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 10 hours time-in-service after the
effective date of this AD, unless accomplished previously.
To prevent failure of the seat restraint system due to the
buckle assembly (buckle) locking mechanism not engaging properly,
which could result in the seat restraint system failing to properly
secure the occupant during turbulence or landing, accomplish the
following:
Note 2: The part number (P/N) of the seat restraint system is on
the identification label located on each end of the seat restraint
system near the anchor point (Example: P/N MD A2626-E010). The model
is designated by the first two letters of the P/N.
(a) Visually check all affected seat restraint systems to
determine if the locking mechanism is engaging properly in
accordance with the following:
(1) Open the lift lever of the buckle fully until it will not
open any further. This will cause the locking mechanism to pivot on
the pivot pin.
(2) Allow the spring to close the lift lever slowly until the
lift lever is back to its at-rest position.
(3) After the lever is completely closed, examine the slot in
the bottom of the buckle. The locking mechanism should be firmly
seated against the edge of the slot as shown in Figure 1.
BILLING CODE 4910-13-U
[[Page 69187]]
[GRAPHIC] [TIFF OMITTED] TR10DE99.022
BILLING CODE 4910-13-C
[[Page 69188]]
(b) If the locking mechanism does not seat properly, replace the
buckle with an airworthy buckle.
(c) The requirements of this AD may be performed by an owner/
operator (pilot) holding at least a private pilot certificate and
must be entered into the aircraft records showing compliance with
this AD in accordance with sections 43.11 and 91.417(a)(2)(v) of the
Federal Aviation Regulations (14 CFR sections 43.11 and
91.417(a)(2)(v)).
Note 3: If the seat restraint systems' locking mechanisms are
found to be functioning properly after the visual check described in
paragraph (a) of this AD, the following is an example of a
maintenance record entry that may be used:
``AD (number), paragraph (a) complied with by visual check. Seat
belt buckle locking mechanism(s) found serviceable. (Date) (Aircraft
total time-in-service). (Signature) (Certificate number and type of
certificate held)''
If any of the seat restraint systems' locking mechanisms are
found to malfunction after the visual check described in paragraph
(a), the following is an example of a maintenance record entry that
may be used:
``AD (number), paragraphs (a) and (b) complied with by visual
check and replacement of seat belt buckle locking mechanism(s) on
(seat location(s)) with airworthy buckle(s). (Date) (Aircraft total
time-in-service). (Signature) (Certificate number and type of
certificate held)''
(d) 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, Airplane Certification Office, FAA.
Operators shall submit their requests through a FAA Principal
Maintenance Inspector, who may concur or comment and then send it to
the Manager, Airplane Certification Office.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Airplane Certification Office.
(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 aircraft to a location where
the requirements of this AD can be accomplished.
(f) This amendment becomes effective on January 14, 2000.
Issued in Fort Worth, Texas, on December 3, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-32083 Filed 12-9-99; 8:45 am]
BILLING CODE 4910-13-U
