[Federal Register Volume 63, Number 225 (Monday, November 23, 1998)]
[Rules and Regulations]
[Pages 64612-64615]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31195]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-SW-20-AD; Amendment 39-10900; AD 98-24-15]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Model 204B,
205A, 205A-1, 205B, and 212 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Bell Helicopter Textron Model 204B, 205A, 205A-1,
and 212 helicopters, that currently establishes a retirement life for
the main rotor masts (masts) and main rotor trunnions (trunnions) based
on time-in-service (TIS) and types of operations. This amendment adds
Model 205B helicopters to the applicability; requires creation of
component history cards or equivalent records using a Retirement Index
Number (RIN) system; establishes a system for tracking increases to the
accumulated RIN; and establishes a maximum accumulated RIN for certain
masts and trunnions. This amendment is prompted by an accident
involving a Model 205A-1 helicopter, in which a mast failure caused a
separation of the main rotor from the helicopter. The actions specified
by this AD are intended to prevent fatigue failure of the mast or
trunnion and subsequent loss of control of the helicopter.
DATES: Effective December 8, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 8, 1998.
Comments for inclusion in the Rules Docket must be received on or
before January 22, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 97-SW-20-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
The service information referenced in this AD may be obtained from
Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101,
telephone (817) 280-3391, fax (817) 280-6466. This information may be
examined at the FAA, Office of the Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137; or at the Office
of the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Charles C. Harrison, Aerospace
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5447, fax
(817) 222-5960.
SUPPLEMENTARY INFORMATION: On December 28, 1988, the FAA issued AD 89-
02-07, Amendment 39-6112 (54 FR 1338, January 13, 1989) and on
September 19, 1989, issued revised AD 89-02-07 R1, Amendment 39-6339
(54 FR 40381, October 2, 1989), to establish a retirement life for
certain masts and trunnions based on TIS and types of operations. Those
actions were prompted by results of fatigue stress tests and fatigue
analysis of the mast and trunnion under ground-air-ground (GAG) and
repeated heavy lift (RHL) loading conditions. On June 27, 1997, the FAA
issued priority letter AD 97-14-12 to supersede AD 89-02-07 as revised
by AD 89-02-07 R1 to establish retirement lives for certain masts and
trunnions that utilize a Retirement Index Number (RIN) system.
Exceeding the retirement life of the mast or
[[Page 64613]]
trunnion could result in fatigue failure of the mast or trunnion and
subsequent loss of control of the helicopter.
Since the issuance of AD 89-02-07 and AD 89-02-07 R1, the
manufacturer has issued the following service bulletins to establish
retirement lives for certain masts and trunnions:
Bell Helicopter Textron Alert Service Bulletin No. 205-90-
40, Revision A, dated March 21, 1991, which is applicable to Model
205A-1 helicopters;
Bell Helicopter Textron Alert Service Bulletin No. 205B-
90-1, Revision A, dated March 21, 1991, which is applicable to Model
205B helicopters; and
Bell Helicopter Textron Alert Service Bulletin No. 212-90-
64, Revision B, dated March 11, 1992, which is applicable to Model 212
helicopters.
Also, since the issuance of the earlier AD's, there has been one
accident involving a Model 205A-1 helicopter, in which a mast failure
caused a separation of the main rotor from the helicopter. The
helicopter, which had been utilized in external load lift operations,
was performing an external load lift operation at the time of the
accident. A subsequent metallurgical examination revealed that the mast
had fractured as a result of fatigue. Analyses and fatigue testing has
confirmed that the retirement lives of the mast and trunnion are more
accurately assessed by monitoring the number of torque events and time-
in-service (TIS) incurred by the helicopter rather than by monitoring
only TIS. Exceeding the retirement life of the mast or trunnion could
result in fatigue failure of the mast or trunnion and subsequent loss
of control of the helicopter. Additionally, the FAA has determined that
Model 205B helicopters should be added to the applicability.
Since an unsafe condition has been identified that is likely to
exist or develop on other Model 204B, 205A, 205A-1, 205B, and 212
helicopters of the same type design, this AD supersedes AD 89-02-07 as
revised by AD 89-02-07 R1 and AD 97-14-12 to require, before further
flight, creation of component history cards or equivalent records using
a RIN system for certain masts and trunnions; to establish a system for
tracking increases to the accumulated RIN; and to establish retirement
lives for the mast and trunnion for each of the affected model
helicopters. The actions are required to be accomplished in accordance
with the service bulletins described previously. The short compliance
time involved is required because the previously described critical
unsafe condition can adversely affect the structural integrity of the
aircraft. Therefore, the actions are required before further flight,
and this AD must be issued immediately.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
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-20-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, Incorporation by
reference, 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 39-6112 (54 FR
1338, January 13, 1989), Amendment 39-6339 (54 FR 40381, October 2,
1989) and by adding a new airworthiness directive (AD), Amendment 39-
10900, to read as follows:
AD 98-24-15 Bell Helicopter Textron: Amendment 39-10900. Docket No.
97-SW-20-AD. Supersedes AD 89-02-07, Amendment 39-6112, Docket No.
87-ASW-63; AD 89-02-07 R1, Amendment 39-6339, Docket No. 87-ASW-63;
and priority letter AD 97-14-12, Docket No. 97-SW-20-AD.
Applicability: Model 204B, 205A, 205A-1, 205B, and 212
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
[[Page 64614]]
provided in paragraph (e) 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 before further flight, unless accomplished
previously.
To prevent fatigue failure of the main rotor mast (mast) or main
rotor trunnion (trunnion), and subsequent loss of control of the
helicopter, accomplish the following:
(a) For Model 204B helicopters:
(1) Create component history cards or equivalent records for the
mast, part number (P/N) 204-011-450-001, -007, or -105 and trunnion,
P/N 204-011-105-001.
(2) Determine and record on the component history cards or
equivalent records the accumulated RIN to-date on the mast and
trunnion as follows:
(i) For mast, P/N 204-011-450-001, multiply the total time-in-
service (TIS) on the mast to-date by 50 (if result contains a
decimal point, round-off to the next higher whole number).
(ii) For mast, P/N 204-011-450-007 or -105, and trunnion, P/N
204-011-105-001, multiply the total TIS on the part to-date by 20
(if the result contains a decimal point, round-off to the next
higher whole number).
(3) After complying with paragraphs (a)(1) and (a)(2) of this
AD, during each operation thereafter, maintain a count of the number
and type of external load lifts and the number of takeoffs that were
performed. At the end of each day's operations, increase the
accumulated RIN on the component history cards or equivalent records
as follows:
(i) Increase the RIN by 1 for each takeoff.
(ii) Increase the RIN by 1 for each external load lift, or
increase the RIN by 2 for each external load lift operation in which
the load is picked up at one elevation and released at another
elevation, and the difference in elevation between the pickup point
and the release point is 200 feet or greater.
(4) Remove the mast, P/N 204-011-450-001, on or before attaining
6,000 hours TIS, or an accumulated RIN of 300,000, whichever occurs
first.
(5) Remove the mast, P/N 204-011-450-007 or -105, or trunnion,
P/N 204-011-105-001, on or before attaining 15,000 hours TIS, or an
accumulated RIN of 300,000, whichever occurs first.
(b) For Model 205A and 205A-1 helicopters:
(1) Create component history cards or equivalent records for the
mast, part numbers (P/N) 204-011-450-007, or -105 and trunnion, P/N
204-011-105-001.
(2) Determine and record on the component history cards or
equivalent records the accumulated RIN to-date on the mast and
trunnion. For mast, P/N 204-011-450-007 or -105, and trunnion, P/N
204-011-105-001, multiply the factored flight hour total to-date,
determined in accordance with paragraphs 1, 2, or 3 of the
Accomplishment Instructions of Bell Helicopter Textron Alert Service
Bulletin No. 205-90-40, Revision A, dated March 21, 1991, by 20 (if
the result contains a decimal point, round-off to the next higher
whole number).
(3) After complying with paragraphs (b)(1) and (b)(2) of this
AD, during each operation thereafter, maintain a count of the number
and type of external load lifts and the number of takeoffs that were
performed. At the end of each day's operations, increase the
accumulated RIN on the component history cards or equivalent records
as follows:
(i) Increase the RIN by 2 for each takeoff performed.
(ii) Increase the RIN by 2 for each external load lift, or
increase the RIN by 4 for each external load lift operation in which
the load is picked up at one elevation and released at another
elevation, and the difference in the elevation between the pickup
point and the release point is 200 feet or greater.
(4) Remove the mast, P/N 204-011-450-007 or -105, or trunnion,
P/N 204-011-105-001, on or before attaining 15,000 hours TIS, or an
accumulated RIN of 300,000, whichever occurs first.
(c) For Model 205B helicopters:
(1) Create component history cards or equivalent records for the
mast, P/N 204-011-450-007, or -105 and trunnion, P/N 204-011-105-
001.
(2) Determine and record on the component history cards or
equivalent records the accumulated RIN to-date on the mast and
trunnion. For mast, P/N 204-011-450-007 or -105, and trunnion, P/N
204-011-105-001, multiply the factored flight hour total to-date,
determined in accordance with paragraph 1, 2, or 3 of the
Accomplishment Instructions of Bell Helicopter Textron Alert Service
Bulletin No. 205B-90-1, Revision A, dated March 21, 1991, by 20 (if
the result contains a decimal point, round-off to the next higher
whole number).
(3) After complying with paragraphs (c)(1) and (c)(2) of this
AD, during each operation thereafter, maintain a count of the number
and type of external load lifts and the number of takeoffs
performed, and at the end of each day's operations, increase the
accumulated RIN on the component history card as follows:
(i) Increase the RIN by 5 for each takeoff performed.
(ii) Increase the RIN by 5 for each external load lift, or
increase the RIN by 10 for each external load lift in which the load
is picked up at one elevation and released at another elevation, and
the difference in the elevation between the pickup point and the
release point is 200 feet or greater.
(4) Remove the mast, P/N 204-011-450-007 or -105, or trunnion,
P/N 204-011-105-001, on or before attaining 15,000 hours TIS, or an
accumulated RIN of 300,000, whichever occurs first.
(d) For Model 212 helicopters:
(1) Create component history cards or equivalent records for the
mast, P/N 204-011-450-007, -105, -113, or -119 and trunnion, P/N
204-011-105-001 or -103.
(2) Determine and record on the component history card or an
equivalent record the accumulated RIN to-date on the mast and
trunnion as follows:
(i) For mast, P/N 204-011-450-007 or -105, and trunnion, P/N
204-011-105-001, multiply the factored flight hour total to-date,
determined in accordance with paragraphs 1, 2, and 3 of the
Accomplishment Instructions of Bell Helicopter Textron Alert Service
Bulletin No. 212-90-64, Revision B, dated March 11, 1992, by 20 (if
the result contains a decimal point, round-off to the next higher
whole number).
(ii) For mast, P/N 204-011-450-113 or -119, and trunnion, P/N
204-011-105-103, multiply the factored flight hour total to-date,
determined in accordance with paragraphs 1, 2, or 3 of the
Accomplishment Instructions in Bell Helicopter Textron Alert Service
Bulletin No. 212-90-64, Revision B, dated March 11, 1992, by 21.2
(if the result contains a decimal point, round-off to the next
higher whole number).
(3) After complying with paragraphs (d)(1) and (d)(2) of this
AD, during each operation thereafter, maintain a count of the number
and type of external load lifts and the number of takeoffs
performed. At the end of each day's operations, increase the
accumulated RIN on the component history cards or equivalent records
as follows:
(i) Increase the RIN by 5 for each takeoff performed.
(ii) Increase the RIN by 5 for each external load lift, or
increase the RIN by 10 for each external load lift in which the load
is picked up at one elevation and released at another elevation, and
the difference in the elevation between the pickup point and the
release point is 200 feet or greater.
(4) Remove the mast, P/N 204-011-450-007 or -105, or trunnion,
P/N 204-011-105-001, on or before attaining 15,000 hours TIS, or an
accumulated RIN of 300,000, whichever occurs first.
(5) Remove the mast, P/N 204-011-450-113 or -119, or trunnion,
P/N 204-011-105-103, on or before attaining 13,000 hours TIS or an
accumulated RIN of 275,000, whichever occurs first.
(e) 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(f) 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 helicopter to a location where
the requirements of this AD can be accomplished.
(g) This AD revises the Airworthiness Limitations sections of
the maintenance manuals by establishing a new retirement life for
the affected masts and trunnions as follows:
Masts: P/N 204-011-450-001--6,000 hours TIS or 300,000 RIN
whichever occurs first.
[[Page 64615]]
P/N 204-011-450-007 or P/N 204-011-450-105--15,000 hours TIS or
300,000 RIN, whichever occurs first.
P/N 204-011-450-113 or P/N 204-011-450-119--13,000 hours TIS or
275,000 RIN, whichever occurs first.
Trunnions: P/N 204-011-105-001--15,000 hours TIS or 300,000 RIN,
whichever occurs first.
P/N 204-011-105-103--13,000 hours TIS or 275,000 RIN, whichever
occurs first.
(h) The actions shall be done in accordance with:
Bell Helicopter Textron Alert Service Bulletin No. 205-
90-40, Revision A, dated March 21, 1991, which is applicable to
Model 205A and 205A-1 helicopters;
Bell Helicopter Textron Alert Service Bulletin No.
205B-90-1, Revision A, dated March 21, 1991, which is applicable to
Model 205B helicopters; and
Bell Helicopter Textron Alert Service Bulletin No. 212-
90-64, Revision B, dated March 11, 1992, which is applicable to
Model 212 helicopters.
This incorporation by reference was approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from Bell Helicopter Textron, Inc.,
P.O. Box 482, Fort Worth, Texas 76101, telephone (817) 280-3391, fax
(817) 280-6466. Copies may be inspected at the FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
(i) This amendment becomes effective on December 8, 1998.
Issued in Fort Worth, Texas, on November 13, 1998.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-31195 Filed 11-20-98; 8:45 am]
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