TDATA NOTE: This corrected copy reflects FAA corrections in the preamble of
the AD. Specifically in sections "Summary paragraph" and "§ 39.13 [Amended]"
The FAA will issue a correction to include the supersedure references to AD
2000-06-10.
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:
ILLUSTRATION (Accomplishment table)
ILLUSTRATION (Figure 1 - preflight check of the tailboom)
(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 §§ 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. 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.
FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, Texas 76193
-0111, telephone (817) 222-5122, fax (817) 222-5961.
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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,
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.
§ 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive to read
as follows: