[Federal Register Volume 62, Number 238 (Thursday, December 11, 1997)]
[Rules and Regulations]
[Pages 65198-65201]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-32255]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-SW-46-AD; Amendment 39-10240; AD 97-20-13]
RIN 2120-AA64
Airworthiness Directives; Eurocopter Deutschland Model EC135 P1
and T1 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) 97-20-13 which was sent
previously to all known U.S. owners and operators of Eurocopter
Deutschland Model EC135 P1 and T1 helicopters by individual letters.
This amendment is prompted by the discovery of cracks on the stator
blades of the fenestron tail rotor (tail rotor). The actions specified
by this AD are intended to prevent failure of the tail rotor and
subsequent loss of control of the helicopter.
DATES: Effective December 29, 1997, to all persons except those persons
to whom it was made immediately effective by priority letter AD 97-20-
13, issued on September 25, 1997, which contained the requirements of
this amendment.
Comments for inclusion in the Rules Docket must be received on or
before February 9, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of Regional Counsel, Southwest Region,
Attention: Rules Docket No. 97-SW-46-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Mr. Richard Monschke, Aerospace
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, (817)
222-5961.
SUPPLEMENTARY INFORMATION: On September 25, 1997, the FAA issued
priority letter AD 97-20-13, applicable to Eurocopter Deutschland Model
[[Page 65199]]
EC135 P1 and T1 helicopters, which requires immediate and daily
repetitive inspections of the stator blades for cracks in the stator
hub area. If this visual inspection reveals a crack, a dye-penetrant
inspection is required. Also, within 400 hours time-in-service (TIS)
after the effective date of this AD, and thereafter, at intervals not
to exceed 400 hours TIS, a dye-penetrant inspection for cracks is
required. If any of the inspections reveal cracked stator blades, each
crack must be stop-drilled. If any of the inspections reveal cracks on
a stator blade with a total crack length of 15mm or longer, or if
cracks are found on more than 3 stator blades, the affected blades must
be replaced with airworthy blades prior to further flight. That action
was prompted by the discovery of cracks on the stator blades of the
tail rotor. This condition, if not corrected, could result in failure
of the tail rotor and subsequent loss of control of the helicopter.
Since the unsafe condition described is likely to exist or develop
on other Eurocopter Deutschland Model EC135 P1 and T1 helicopters of
the same type design, the FAA issued priority letter AD 97-20-13 to
prevent failure of the tail rotor and subsequent loss of control of the
helicopter. The AD requires, before further flight, and thereafter,
before the first flight of each day, visually inspecting the stator
blades in the stator hub area. If this visual inspection reveals a
crack, a dye-penetrant inspection is required. Also, within 400 hours
TIS after the effective date of this AD, and thereafter, at intervals
not to exceed 400 hours TIS, a dye-penetrant inspection for cracks is
required. If any of the inspections reveal cracked stator blades, each
crack must be stop-drilled. If any of the inspections reveal cracks on
a stator blade with a total crack length of 15mm or longer, or if
cracks are found on more than 3 stator blades, the affected stator
blades must be replaced with airworthy stator blades prior to further
flight.
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 September 25, 1997 to all known U.S. owners and operators of
Eurocopter Deutschland Model EC135 P1 and T1 helicopters. These
conditions still exist, and the AD is hereby 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.
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. 97-SW-46-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 adding a new airworthiness directive
to read as follows:
97-20-13--Eurocopter Deutschland: Amendment 39-10240. Docket No. 97-
SW-46-AD.
Applicability: Model EC135 P1 and T1 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 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 prevent failure of the tail rotor and subsequent loss of
control of the helicopter, accomplish the following:
(a) Before further flight, and thereafter before the first
flight of each day, visually inspect all stator blades in the stator
hub area for cracks (see Figure 1). Inspect the stator blades in the
areas where they are riveted to
[[Page 65200]]
the stator hub. Pay particular attention to the radius areas where
the stator blade base attaches to the stator hub.
(1) If the inspection reveals a crack at the base of a stator
blade, remove the paint from the area and perform a dye-penetrant
inspection.
(2) If the inspection reveals 3 or less cracked stator blades
and a total crack length per stator blade of less than 15mm, stop-
drill each crack with a 2mm diameter drill.
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[GRAPHIC] [TIFF OMITTED] TR11DE97.000
[[Page 65201]]
(b) Within 400 hours time-in-service (TIS), and thereafter, at
intervals not to exceed 400 hours TIS, remove the paint from all
stator blades in the stator hub area and perform a dye-penetrant
inspection for cracks.
(c) If the inspections reveal cracks on any stator blade with a
total crack length of 15mm or longer, or if more than 3 stator
blades are cracked, remove the affected stator blades and replace
them with airworthy stator blades before further flight. The
inspections required by this AD must continue to be performed on all
stator blades including replacement stator blades.
Note 2: Eurocopter Deutschland Alert Service Bulletin No. EC
135-53A-001, Revision 01, dated August 8, 1997, pertains to this AD.
(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,
Rotorcraft Directorate, 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 December 29, 1997, to
all persons except those persons to whom it was made immediately
effective by Priority Letter AD 97-20-13, issued September 25, 1997,
which contained the requirements of this amendment.
Note 4: The subject of this AD is addressed in Luftfahrt-
Bundesamt (Germany) AD 97-249, effective September 25, 1997.
Issued in Fort Worth, Texas, on December 2, 1997.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-32255 Filed 12-10-97; 8:45 am]
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