[Federal Register Volume 63, Number 212 (Tuesday, November 3, 1998)]
[Rules and Regulations]
[Pages 59206-59208]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-29375]
[[Page 59206]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-35-AD; Amendment 39-10866; AD 98-15-25]
RIN 2120-AA64
Airworthiness Directives; Eurocopter Deutschland GmbH Model EC
135 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This document publishes in the Federal Register an amendment
adopting Airworthiness Directive (AD) 98-15-25, which was sent
previously to all known U.S. owners and operators of Eurocopter
Deutschland GmbH Model EC 135 helicopters by individual letters. This
AD supersedes AD 98-09-11, applicable to Eurocopter Deutschland GmbH
Model EC 135 helicopters, that required, before further flight, a tail
rotor drive shaft vibration survey and installation of a Fenestron
Shaft Retrofit Kit; inspecting the tail rotor drive shaft bearing
(bearing) attaching lock plates for bent-open tabs, and broken or
missing slippage marks; and visually inspecting each bearing support
for cracks. This AD requires the same actions as the superseded AD,
however it changes the required compliance time for the repetitive
inspections. This amendment is prompted by reports of loose bearings
and attachment bolts. This condition, if not corrected, could result in
loose bearing attachment bolts, or cracked bearing supports, which
could result in loss of drive to the tail rotor and subsequent loss of
control of the helicopter.
DATES: Effective November 18, 1998, to all persons except those persons
to whom it was made immediately effective by priority letter AD 98-15-
25, issued on July 17, 1998, which contained the requirements of this
amendment.
Comments for inclusion in the Rules Docket must be received on or
before January 4, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-35-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Mr. Scott Horn, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5125, fax (817)
222-5961.
SUPPLEMENTARY INFORMATION: On July 17, 1998, the FAA issued priority
letter AD 98-15-25, applicable to Eurocopter Deutschland GmbH Model EC
135 helicopters, which requires, before further flight, a tail rotor
drive shaft vibration survey and installation of a Fenestron Shaft
Retrofit Kit L 535M3002 882; before further flight, and thereafter at
intervals not to exceed 15 hours time-in-service (TIS), inspecting the
bearing attaching lock plates for bent-open tabs, and broken or missing
slippage marks; and before further flight, and thereafter at intervals
not to exceed 3 hours TIS, visually inspecting each bearing support for
cracks. That action was prompted by several reports of loose tail rotor
drive shaft bearings and attachment bolts. This condition, if not
corrected, could result in loose bearing attachment bolts, or cracked
bearing supports, which could result in loss of drive to the tail rotor
and subsequent loss of control of the helicopter.
The FAA previously issued AD 98-09-11 on June 18, 1998 (63 FR
34796, June 26, 1998). AD 98-09-11 contained the same requirements as
this AD except that this AD requires the repetitive visual inspection
of each bearing support to be conducted at intervals not to exceed 3
hours TIS instead of the previous 15 hours TIS.
Since the issuance of AD 98-09-11, it has been determined that
cracks can form in additional areas outside the bend radius of the
bearing support, and that the cracks can form and propagate to failure
within the previously-required 15 hours TIS inspection interval.
The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority
for the Federal Republic of Germany, recently notified the FAA that an
unsafe condition may exist on Eurocopter Deutschland GmbH Model EC 135
helicopters. The LBA advises that loosening of bolt connections at
bearing supports may lead to a tail rotor failure and loss of the
helicopter. The LBA issued AD 1998-033/6, dated July 9, 1998,
applicable to ECD Model EC 135 helicopters.
The FAA has reviewed Eurocopter EC 135 Alert Service Bulletin No.
EC 135-53A-002, Revision 1, dated July 7, 1998, which describes
procedures for visually inspecting the bearing supports, and Eurocopter
EC 135 Alert Service Bulletin No. EC 135-53A-005, Revision 1, dated
April 6, 1998, which describes procedures for measuring vibrations on
the tail rotor drive shaft and replacing roller bearing attaching
hardware at bearing locations.
This helicopter model is manufactured in the Federal Republic of
Germany and is type certificated for operation in the United States
under the provision of section 21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the applicable bilateral airworthiness
agreement. Pursuant to this bilateral airworthiness agreement, the LBA
has kept the FAA informed of the situation described above. The FAA has
examined the findings of the LBA, reviewed all available information,
and determined that AD action is necessary for products of this type
design that are certificated for operations in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other Eurocopter Deutschland GmbH Model EC 135
helicopters of the same type design, this AD requires, before further
flight, a tail rotor drive shaft vibration survey and installation of a
Fenestron Shaft Retrofit Kit L 535M3002 882. Also, before further
flight, and thereafter at intervals not to exceed 15 hours TIS, the AD
requires inspecting the bearing attaching lock plates at each bearing
support for bent-open tabs, and inspecting for broken or missing
slippage marks. If a bearing attaching lock plate tab is bent open, or
if a slippage mark is broken or missing, the FAA must be notified.
Finally, the AD requires, before further flight, and thereafter at
intervals not to exceed 3 hours TIS, inspecting the bearing supports
for cracks in the areas shown in the attached Figure 1, from the bend
radius to the attaching screws and rivets connecting the bearing
supports to the tailboom. Use of a 6-power or higher magnifying glass
and a bright light are required for this inspection. If a crack is
found, the cracked bearing support is to be replaced with an airworthy
bearing support.
The short compliance time involved is required because the
previously described critical unsafe condition can adversely affect the
structural integrity and controllability of the aircraft. Therefore,
the installation and an inspection are required before further flight,
and this AD must be issued immediately.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual letters
issued on July 17, 1998 to all known U.S. owners and operators of
Eurocopter Deutschland GmbH Model EC 135 helicopters. These conditions
still exist, and the AD is hereby
[[Page 59207]]
published in the Federal Register as an amendment to section 39.13 of
the Federal Aviation Regulations (14 CFR 39.13) to make it effective to
all persons. The only difference between the priority letter AD and
this published version of this AD is that a NOTE 2 is added to this AD
to inform the reader that the procedures and limits for the vibration
survey are contained in Eurocopter Deutschland document D/TA 13/98,
Revision 01. This note is informational only and is not a substantive
change.
The FAA estimates that 6 helicopters of U.S. registry will be
affected by this AD. The 15 hours TIS inspection will take
approximately 0.5 work hours and the 3 hours TIS inspection will take
approximately 1.5 work hours. The average labor rate is $60 per work
hour. The manufacturer has represented that they will accomplish this
vibration survey and the installation of the Fenestron Shaft Retrofit
kit at no cost to the owners/operators. Assuming the helicopters are
operated 900 hours TIS per year, the total cost impact of the AD on
U.S. operators for one year is estimated to be $172,800.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 98-SW-35-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, 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, 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 39-10632 (63 FR
34796, June 26, 1998) and by adding a new airworthiness directive to
read as follows:
98-15-25 Eurocopter Deutschland: Amendment 39-10866. Docket No. 98-
SW-35-AD. Supersedes AD 98-09-11, Amendment 39-10632, Docket No. 98-
SW-18-AD.
Applicability: Model EC 135 helicopters, certificated in any
category.
Note 1: This AD applies to each helicopter 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 helicopters that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must use the authority
provided in paragraph (d) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition, or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any helicopter from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To detect loose tail rotor drive shaft bearing (bearing)
attachment bolts, or cracked bearing supports, which could result in
loss of drive to the tail rotor and subsequent loss of control of
the helicopter, accomplish the following:
(a) Before further flight, conduct a tail rotor drive shaft
vibration survey and install a Fenestron Shaft Retrofit Kit L
535M3002 882.
Note 2: Procedures and limits for the vibration survey are
provided in Eurocopter Deutschland document D/TA 13/98 Revision 01.
(b) Before further flight, and thereafter at intervals not to
exceed 15 hours time-in-service (TIS), at each bearing support:
(1) Inspect each bearing attaching lock plate that was installed
with the Fenestron Shaft Retrofit Kit L 535M3002 882 for bent-open
tabs.
(2) Inspect for broken or missing slippage marks that may
indicate looseness or rotation of attaching hardware.
(3) If a lock plate tab is bent open on bearing supports A, B,
or C (shown in Figure 1), or if slippage marks are broken or
missing, contact the Manager, Rotorcraft Standards Staff, FAA,
telephone (817) 222-5110, fax (817) 222-5961.
[[Page 59208]]
[GRAPHIC] [TIFF OMITTED] TR03NO98.028
(c) Before further flight, and thereafter at intervals not to
exceed 3 hours TIS, using a 6-power or higher magnifying glass and a
bright light, visually inspect bearing supports B and C as shown in
Figure 1, from the bend radius to the attaching screws and rivets
connecting the bearing supports to the tailboom. If a crack is
found, replace the bearing support with an airworthy bearing
support.
(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, Rotorcraft Standards Staff, FAA.
Operators shall submit their requests through an FAA Principal
Maintenance Inspector, who may concur or comment and then send it to
the Manager, Rotorcraft Standards Staff.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(e) Special flight permits will not be issued.
(f) This amendment becomes effective on November 18, 1998, to
all persons except those persons to whom it was made immediately
effective by Priority Letter AD 98-15-25, issued July 17, 1998,
which contained the requirements of this amendment.
Note 4: The subject of this AD is addressed in Luftfahrt-
Bundesamt (Federal Republic of Germany) AD 1998-033/6, dated July 9,
1988.
Issued in Fort Worth, Texas, on October 27, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-29375 Filed 11-2-98; 8:45 am]
BILLING CODE 4910-13-P
