[Federal Register Volume 75, Number 198 (Thursday, October 14, 2010)]
[Rules and Regulations]
[Pages 63045-63048]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-25469]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0642; Directorate Identifier 2007-NM-332-AD;
Amendment 39-16470; AD 2010-21-10]
RIN 2120-AA64
Airworthiness Directives; BAE SYSTEMS (OPERATIONS) LIMITED Model
BAe 146 and Avro 146-RJ Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
* * * [F]uel leaks and failed fasteners [have been reported] in
the region of the rear spar root joint attachment fitting at wing
rib 2. * * *
* * * * *
The unsafe condition is stress corrosion failures in the region of the
rear spar root joint attachment fitting at wing rib 2, which could lead
to reduced structural integrity of the wing, and consequent reduced
controllability of the airplane. We are issuing this AD to require
actions to correct the unsafe condition on these products.
DATES: This AD becomes effective November 18, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 18,
2010.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on July 1, 2010 (75 FR
38058). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
British Aerospace originally issued Service Bulletin (SB) 57-033
in 1989 to detect fuel leaks and failed fasteners in the region of
the rear spar root joint attachment fitting at wing rib 2.
Accomplishment of this SB was mandated by the [Civil Aviation
Authority] CAA United Kingdom AD 044-09-89. Revisions 1 through 7 of
this SB were introduced to inspect pre mod HCM01447A standard
installations for fuel leaks and loose or broken bolts. Modification
HCM01447A
[[Page 63046]]
introduced tension bolts in the attachment fitting instead of the
previous Hi-Lok bolts.
Revision 8 of the SB introduced inspection instructions for post
modification HCM01447A installations because fuel tank leaks and
failed fasteners have subsequently been found on aircraft post
modification HCM01447A. Inspections of the post-mod HCM01447A
standard are required to maintain the structural integrity of the
wing. BAE Systems has now published SB 57-033 Revision 9 that
specifies additional, calendar-time based, inspection criteria to
control the stress corrosion failures of the pre and post
modification HCM01447A installations.
EASA AD 2007-0270 supersedes CAA UK AD 044-09-89 and requires
the accomplishment of inspections and corrective actions, as
necessary, in accordance with BAE Systems SB 57-033 Revision 9.
This [EASA] AD [2007-0270 R1] is revised to clarify that the
calendar compliance times are to be counted from the effective date,
not from the SB issue date.
The unsafe condition is stress corrosion failures in the region of the
rear spar root joint attachment fitting at wing rib 2, which could lead
to reduced structural integrity of the wing, and consequent reduced
controllability of the airplane. Required actions include a general
inspection to identify the type of bolt and nut at each location,
external inspections of the bolt installation of the fuel tanks,
related investigative actions, and corrective actions, as applicable.
The general inspection includes identifying the type of bolt and
nut at each location.
External inspections of the bolt installation include:
Visually inspecting for proper nut installation, nut
seating, and fuel seepage.
Checking for gaps between the fitting and wing structure.
Checking the nuts with a suitable torque spanner to the
specifications in the torque figures shown in Table 2. of the
Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED
Inspection Service Bulletin ISB.57-033, Revision 9, dated October 10,
2006, if Hi-Loks are installed, and
Doing either an ultrasonic inspection for damaged bolts or
torque check of the tension bolts.
Related investigative actions include:
Inspecting the condition of the sealant at and around all
rear spar root joint attachment bolts.
Checking the bolt for damage or evidence of the nut being
tightened to the end of the thread.
Examining the wear pattern on the seating surfaces of the
bolt and nut to determine if the bolt and nut have been evenly seated
on the structure.
Visually inspecting the bolt hole and surrounding area for
damage, and
Confirming that the hole edge radius on the forward face
of the rear spar complies with the specifications in Table 4 of the
Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED
Inspection Service Bulletin ISB.57-033, Revision 9, dated October 10,
2006.
Corrective actions include either replacing the bolt, or repairing
the defect in accordance with approved repair data from BAE Systems.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Explanation of Change to Applicability
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Conclusion
We reviewed the available data, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 1 product of U.S. registry. We
also estimate that it will take about 3 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $255.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
[[Page 63047]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2010-21-10 BAE SYSTEMS (OPERATIONS) LIMITED: Amendment 39-16470.
Docket No. FAA-2010-0642; Directorate Identifier 2007-NM-332-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
18, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems (OPERATIONS) LIMITED
Model BAe 146-100A, -200A, and -300A airplanes, and Model Avro 146-
RJ70A, 146-RJ85A, and 146-RJ100A airplanes, certificated in any
category.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
* * * [F]uel leaks and failed fasteners [have been reported] in
the region of the rear spar root joint attachment fitting at wing
rib 2. * * *
* * * * *
The unsafe condition is stress corrosion failures in the region of
the rear spar root joint attachment fitting at wing rib 2, which
could lead to reduced structural integrity of the wing, and
consequent reduced controllability of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Actions
(g) At the applicable time in paragraph (g)(1) or (g)(2) of this
AD, do a general visual inspection to identify the type of bolt and
nut at each location, in accordance with the Accomplishment
Instructions of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service
Bulletin ISB.57-033, Revision 9, dated October 10, 2006.
(1) For airplanes on which neither Modification HCM01447A nor
repair information leaflet (RIL) HC536H9156 (at any location) has
been done as of the effective date of this AD, the compliance time
for the inspection is at the later of the times specified in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) Within 12 months after the effective date of this AD, or
within 2 years after the last inspection done in accordance with BAE
SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033,
whichever occurs later, without exceeding 4,000 flight cycles after
the last inspection.
(ii) Within 250 flight cycles or 3 months after the effective
date of this AD, whichever occurs first.
(2) For airplanes on which either Modification HCM01447A or RIL
HC536H9156 (at any location) has been done as of the effective date
of this AD, the compliance time for the inspection is at the latest
of the times specified in paragraphs (g)(2)(i), (g)(2)(ii), and
(g)(2)(iii) of this AD.
(i) Before the accumulation of 4,000 total flight cycles.
(ii) Within 4,000 flight cycles after all bolts are inspected
and replaced in accordance with BAE SYSTEMS (OPERATIONS) LIMITED
Inspection Service Bulletin ISB.57-033.
(iii) Within 12 months after the effective date of this AD.
(h) At the applicable time in paragraph (g)(1) or (g)(2) of this
AD, do detailed inspections of the bolt installation for proper nut
installation, nut seating, and fuel seepage; a detailed inspection
for gaps between the fitting and wing structure; if Hi-Loks are
installed, measure the torque of the nuts to determine the
specifications in the torque figures shown in Table 2. of the
Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED
Inspection Service Bulletin ISB.57-033, Revision 9, dated October
10, 2006; and either an ultrasonic inspection for damaged bolts or a
torque measurement of the tension bolts to determine the
specifications in the torque figures shown in Table 3 of the
Accomplishment Instructions of BAE SYSTEMS (OPERATIONS) LIMITED
Inspection Service Bulletin ISB.57-033, Revision 9, dated October
10, 2006. Do all actions in accordance with the Accomplishment
Instructions of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service
Bulletin ISB.57-033, Revision 9, dated October 10, 2006.
(i) If, during any inspection required by paragraph (h) of this
AD, any defect (e.g., evidence of fuel seepage, damaged bolts or low
bolt torque, loose or rotating nuts, suspect integrity of the bolt/
nut assembly, or gaps between the fitting and wing structure) is
found, before further flight, do the actions specified in paragraphs
(i)(1), (i)(2), (i)(3), (i)(4), and (i)(5) of this AD, in accordance
with the Accomplishment Instructions of BAE SYSTEMS (OPERATIONS)
LIMITED Inspection Service Bulletin ISB.57-033, Revision 9, dated
October 10, 2006.
(1) Do a detailed inspection of the sealant for cracks at and
around all rear spar root joint attachment bolts.
(2) Do a detailed inspection of the bolt for damage or evidence
of the nut being tightened to the end of the thread.
(3) Do a detailed inspection of the wear pattern on the seating
surfaces of the bolt and nut to determine if the bolt and nut have
been evenly seated on the structure.
(4) Do a detailed inspection of the bolt hole and surrounding
area for damage.
(5) Do a detailed inspection to determine that the hole edge
radius on the forward face of the rear spar meets the dimensions
specified in Table 4 of the Accomplishment Instructions of BAE
SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033,
Revision 9, dated October 10, 2006.
(j) If during any inspection required by paragraph (h) or (i) of
this AD, any defects (e.g., evidence of fuel seepage, damaged bolts
or low bolt torque, loose or rotating nuts, suspect integrity of the
bolt/nut assembly, gaps between the fitting and wing structure,
cracked sealant, bolt damage or evidence of the nut being tightened
to the end of the thread, uneven seating of the bolt and nut, bolt
hole and surrounding area damage, or hole edge radius out of
dimensions specified in Table 4 of the Accomplishment Instructions
of BAE SYSTEMS (OPERATIONS) LIMITED Inspection Service Bulletin
ISB.57-033, Revision 9, dated October 10, 2006), is found, before
further flight, do all applicable correction actions, which include
either replacing the bolt or repairing the defect, in accordance
with the Accomplishment Instructions of BAE SYSTEMS (OPERATIONS)
LIMITED Inspection Service Bulletin ISB.57-033, Revision 9, dated
October 10, 2006.
(k) Repeat the inspections in paragraph (h) of this AD
thereafter, at the applicable time specified in Table 1 of this AD,
for each individual location.
Table 1--Compliance Times for Repeat Inspections
------------------------------------------------------------------------
If the location has-- Then repeat the inspection--
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A Hi-Lok bolt.......................... Within 4,000 flight cycles or
24 months, whichever occurs
earlier, after doing the last
inspection.
A tension bolt that was not replaced Within 8,000 flight cycles or
during the inspections in paragraphs 48 months, whichever occurs
(h) and (i) of this AD and no defects earlier, after doing the last
were found. inspection.
[[Page 63048]]
A tension bolt that was replaced as Within 4,000 flight cycles or
required by paragraph (j) of this AD. 24 months, whichever occurs
earlier after doing the
replacement.
A tension bolt that was not replaced Within 4,000 flight cycles or
and any defects were repaired as 24 months, whichever occurs
required by paragraph (j) of this AD. earlier after doing the repair
specified in paragraph (j) of
this AD.
------------------------------------------------------------------------
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: Although BAE SYSTEMS (OPERATIONS) LIMITED Service
Bulletin ISB.57-033, Revision 9, dated October 10, 2006, allows
additional time to rectify the defect for the corrective action
depending on the condition, this AD requires rectifying the defect
before further flight.
Other FAA AD Provisions
(l) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN: Todd
Thompson, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(m) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2007-0270 R1, dated November 7, 2007; and BAE SYSTEMS
(OPERATIONS) LIMITED Inspection Service Bulletin ISB.57-033,
Revision 9, dated October 10, 2006; for related information.
Material Incorporated by Reference
(n) You must use BAE SYSTEMS (OPERATIONS) LIMITED Inspection
Service Bulletin ISB.57-033, Revision 9, dated October 10, 2006; to
do the actions required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact BAE
SYSTEMS (OPERATIONS) LIMITED, Customer Information Department,
Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United
Kingdom; telephone +44 1292 675207; fax +44 1292 675704; e-mail
[email protected]; Internet http://www.baesystems.com/Businesses/RegionalAircraft/index.htm.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on September 29, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-25469 Filed 10-13-10; 8:45 am]
BILLING CODE 4910-13-P