[Federal Register: March 13, 2003 (Volume 68, Number 49)]
[Rules and Regulations]
[Page 11967-11971]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13mr03-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-SW-53-AD; Amendment 39-13079; AD 2003-05-03]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada Model
407 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) for
the specified Bell Helicopter Textron Canada (Bell) model helicopters
that requires preflight checking and repetitively inspecting for a
crack in certain tailbooms that have not been redesigned and replacing
the tailboom if a crack is found; modifying and re-identifying certain
tailbooms and installing an improved horizontal stabilizer assembly;
and assigning a 5,000 hour time-in-service (TIS) life limit. This
amendment is prompted by cracking discovered in other areas of certain
tailbooms and introduction of a redesigned tailboom with a chemically
milled skin, which does not require the current inspections. The
actions specified by this AD are intended to prevent separation of the
tailboom and subsequent loss of control of the helicopter.
DATES: Effective April 17, 2003.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 17, 2003.
ADDRESSES: The service information referenced in this AD may be
obtained from Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir,
Mirabel, Quebec J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax
(450) 433-0272. This information may be examined 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.
FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety
Engineer,
[[Page 11968]]
FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, Texas
76193-0111, telephone (817) 222-5122, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: On March 21, 2000, the FAA issued AD 2000-
06-10, Amendment 39-11651 (65 FR 16804, March 30, 2000), to require
preflight checking and repetitively inspecting the tailboom for a crack
and replacing the tailboom if a crack is found. That action was
prompted by four reports of cracks on the tailboom in the area of the
horizontal stabilizer. The requirements of that AD were intended to
prevent separation of the tailboom and subsequent loss of control of
the helicopter. Next, a proposal to amend 14 CFR part 39 to include an
AD for Bell Model 407 helicopters was published in the Federal Register
on January 31, 2002 (67 FR 4685). That NPRM would have required
preflight checking and repetitively inspecting for a crack in certain
tailbooms that have not been redesigned and replacing the tailboom if a
crack is found. It further proposed that installing tailboom, P/N 407-
030-801-201, would constitute terminating action for the requirements
of that AD.
Since the issuance of that NPRM on January 31, 2002 (67 FR 4685),
the manufacturer has issued Bell Helicopter Textron Alert Service
Bulletin (ASB) No. 407-99-26, Revision C, dated February 28, 2002, that
addresses inspection procedures for certain tailbooms. The manufacturer
also issued Bell Helicopter Textron ASB No. 407-01-48, Revision B,
dated April 25, 2002, that details the modification and re-
identification of those certain tailbooms, assigns a life limit, and
details new inspection procedures for those re-identified tailbooms.
Additionally, ASB 407-01-48 assigns a life limit and details new
inspection procedures for another part-numbered tailboom that was
modified by the manufacturer. Further, in addition to the redesigned
tailboom, P/N 407-030-801-201, referenced in the NPRM, Bell has at
least one additional redesigned tailboom, P/N 407-030-801-203, for
these helicopters. Transport Canada, which is the airworthiness
authority for Canada, has issued a revised AD No. CF-1999-17R2, dated
April 5, 2002, to address these changed requirements.
After reviewing comments received in response to that proposal as
well as updated service information from the manufacturer, on November
14, 2002 (67 FR 68952), the FAA published a supplemental notice in the
Federal Register to propose mandating daily pre-flight checks and
initial 25-hour TIS inspections with recurring 50 hour TIS inspections
for the tailbooms, P/N 407-030-801-101 and -105, until they are
modified and re-identified. Once modified and re-identified as P/N 407-
530-014-101 and -103, respectively, the FAA proposed to mandate the
150-hour TIS inspection and assign a 5,000-hour TIS life limit. The
150-hour TIS inspection and 5,000 hour life limit also applies to the
tailboom, P/N 407-030-801-107. Additionally, the cite to tailboom, P/N
407-030-801-201, as a terminating action was removed since the
installation of other redesigned tailbooms may also effectively remove
a helicopter from the applicability of this proposal, thereby
constituting a terminating action for the requirements of this AD.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Two commenters state that the instructions need to be clear
regarding the assignment of the life limit. The FAA agrees and has
changed paragraph (d) of the AD to clarify the tailboom life limit. For
the modified tailbooms, P/N 407-530-014-101 and P/N 407-530-014-103,
5,000 hours TIS since modified and installed is the life limit. The
life limit for tailboom, P/N 407-030-801-107, is 5,000 hours since new
(initially installed on any helicopter).
One commenter states that the proposed compliance date may be too
short. Additionally, the commenter points out an incorrect reference in
the preamble discussion to the part number tailboom cited for use as a
terminating action. The FAA agrees; P/N 407-030-801-101 cited in the
discussion should have been P/N 407-030-801-201. Also, the FAA agrees
that the compliance time was too short. Because the compliance time
cited in the proposal was ``January 31, 2003'' and that date has
passed, the required compliance time for paragraph (c) of the AD is
changed to ``within 30 days.''
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 with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
The FAA estimates that 284 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 3.5 work hours per
helicopter to accomplish the initial inspections, 1.5 work hours per
helicopter to accomplish the recurring inspections, and 18 work hours
per helicopter to accomplish the modification, and that the average
labor rate is $60 per work hour. Required parts will cost approximately
$1,244 per helicopter. Based on these figures, the total cost impact of
the AD on U.S. operators is estimated to be $3,254 per helicopter, or
$924,136, assuming all U.S. registered helicopters are required to be
modified and initially inspected, and have 8 repetitive inspections per
year. In its service information, under certain conditions, the
manufacturer offers a ``special'' warranty for parts needed for
modifying tailbooms, P/N 407-030-801-101 and -105, and a labor
allowance of $480.
The regulations adopted herein will not have a substantial direct
effect 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, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
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 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.
[[Page 11969]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
2003-05-03 Bell Helicopter Textron Canada: Amendment 39-13079.
Docket No. 2001-SW-53-AD. Supersedes AD 2000-06-10, Docket No. 99-
SW-75-AD, Amendment 39-11651.
Applicability: Model 407 helicopters, serial numbers 53000
through 53475, with tailboom, part number (P/N) 407-030-801-101, -
105 or-107, or P/N 407-530-014-101 or -103, (re-identified in
accordance with Bell Helicopter Textron (Bell) Alert Service
Bulletin (ASB) 407-01-48, Revision B, dated April 25, 2002),
installed, certificated in any category.
Note 1: This AD applies to each helicopter 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 helicopters 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 (h) 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 as indicated.
To prevent separation of the tailboom and subsequent loss of
control of the helicopter, accomplish the following:
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Applicable tailboom Compliance time Actions In accordance with
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(a) Tailboom, P/N 407-030-801-101 and Before the first flight Visually check the Figure 1 of this AD.
-105, that have not been modified in of each day. tailboom for cracks.
accordance with Bell ASB 407-01-048, An owner/operator
Revision B, dated April 25, 2002. (pilot) holding at
least a private pilot
certificate may
perform the visual
check required by this
paragraph, but must
enter compliance with
this paragraph into
the helicopter records
in accordance with 14
CFR 43.11 and
91.417(a)(2)(v).
(b) Tailboom, P/N 407-030-801-101 and Within 25 hours time-in- Visually inspect the Part II of the
-105, that have 600 or more hours service (TIS), and tailboom for cracks Accomplishment
TIS and have not been modified in thereafter at using a 10x or higher Instructions of Bell
accordance with Bell ASB 407-01-48, intervals not to magnifying glass. ASB 407-99-26,
Revision B, dated April 25, 2002. exceed 50 hours TIS. Revision C, dated
February 28, 2002,
except contacting Bell
is not required.
(c) Tailboom, P/N 407-030-801-101 and Within 600 hours TIS, Modify and re-identify Parts I and III of the
-105. but not later than 30 tailbooms as P/N 407- Accomplishment
days, unless 530-014-101 and -103, Instructions in Bell
previously respectively, and ASB 407-01-48,
accomplished. install improved Revision B, dated
horizontal stabilizer April 25, 2002, and
assembly, P/N 407-023- Bell Technical
800-ALL. Bulletin No. 407-01-
33, dated August 29,
2001, except
contacting Bell is not
required.
(d) Tailboom, P/N 407-530-014-101 and Before further flight Create a historical Part IV of the
-103; and P/N 407-030-801-107. after the tailboom is service record sheet Accomplishment
modified and re- and assign a life Instructions in Bell
identified, unless limit of 5,000 hours ASB 407-01-48,
previously TIS since Revision B, dated
accomplished. modification, re- April 25, 2002.
identification, and
installation of
tailboom, P/N 407-530-
014-101 or -103, on
any helicopter, or
initial installation
of P/N 407-030-801-107
on any helicopter.
(e) Tailboom, P/N 407-530-014-101 and Within 150 hours TIS Inspect the tailboom Parts IV and V of the
103; and P/N 407-030-801-107. after modification, or for a crack. Accomplishment
within 150 hours TIS Instructions in Bell
since new, and ASB 407-01-48,
thereafter at Revision B, dated
intervals not to April 25, 2002.
exceed 150 hours TIS.
(f) All applicable part-numbered Before further flight.. If a crack is found, The applicable
tailbooms. replace the tailboom. maintenance manual.
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(g) This AD revises the helicopter Airworthiness Limitations
section of the maintenance manual by establishing a new retirement
life for the tailboom, P/N 407-530-014-101 and -103, and P/N 407-
030-801-107 of 5,000 hours TIS.
(h) 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, Regulations Group, 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, Regulations Group.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Regulations Group.
(i) Special flight permits may be issued in accordance with
Sec. Sec. 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.
(j) The inspections shall be done in accordance with Part II of
the Accomplishment Instructions in Bell Helicopter Textron Alert
Service Bulletin No.
[[Page 11971]]
407-99-26, Revision C, dated February 28, 2002. The modifications
and re-identifications shall be accomplished in accordance with Bell
Helicopter Textron Technical Bulletin No. 407-01-33, dated August
29, 2001, and Parts I and III of the Accomplishment Instructions in
Bell Helicopter Textron Alert Service Bulletin 407-01-48, Revision
B, dated April 25, 2002. The creation of historical service record
sheets and inspections shall be done in accordance with Parts IV and
V of the Accomplishment Instructions in Bell Helicopter ASB 407-01-
48, Revision B, dated April 25, 2002. These incorporations by
reference were 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 Canada, 12,800 Rue de
l'Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437-2862 or (800)
363-8023, fax (450) 433-0272. 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.
(k) This amendment becomes effective on April 17, 2003.
Note 3: The subject of this AD is addressed in Transport Canada
(Canada) AD No. CF-1999-17R2, dated April 5, 2002.
Issued in Fort Worth, Texas, on March 3, 2003.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-5576 Filed 3-12-03; 8:45 am]
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