[Federal Register: September 20, 2006 (Volume 71, Number 182)]
[Proposed Rules]
[Page 54939-54941]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20se06-24]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 54939]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25851; Directorate Identifier 2006-NM-133-AD]
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: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ
airplanes. This proposed AD would require determining the part number
of the lift spoiler actuators/jacks (referred to after this as ``lift
spoiler jacks''). For affected lift spoiler jacks, this proposed AD
would require determining the date of manufacture of the lift spoiler
jacks, repetitively inspecting the eye-end assembly of the lift spoiler
jacks to detect discrepancies of the assembly or associated parts, and
performing corrective actions if necessary. This proposed AD results
from a report that a lift spoiler deployed in flight due to corrosion
at the thread where the eye-end assembly was screwed into the piston of
the lift spoiler jack. We are proposing this AD to prevent detachment
of the eye-end assembly of a lift spoiler jack, which could result in
uncommanded deployment of a lift spoiler in flight, and consequent
reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by October 20,
2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact British Aerospace Regional Aircraft American Support, 13850
Mclearen Road, Herndon, Virginia 20171, for service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
25851; Directorate Identifier 2006-NM-133-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit http://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
The European Aviation Safety Agency (EASA) notified us that an
unsafe condition may exist on all BAE Systems (Operations) Limited
Model BAe 146 and Avro 146-RJ airplanes. The EASA advises that a lift
spoiler deployed in flight, due to detachment of the eye-end assembly
of the lift spoiler actuator/jack (referred to after this as the ``lift
spoiler jack''). Investigation revealed corrosion at the thread where
the eye-end assembly was screwed into the piston of the lift spoiler
jack. This condition, if not corrected, could result in uncommanded
deployment of a lift spoiler in flight, and consequent reduced
controllability of the airplane.
Relevant Service Information
BAE Systems (Operations) Limited has issued Inspection Service
Bulletin SB27-176, Revision 2, dated October 5, 2004. The service
bulletin describes procedures for determining the serial number and
date of manufacture of the lift spoiler jacks, and repetitively
inspecting for discrepancies of the eye-end assembly of certain lift
spoiler jacks, associated hardware (lock nut, locking device, and lock
washer), and the thread of the piston where the eye-end assembly
attaches. Discrepancies include but are not limited to evidence of
corrosion or damaged or fretted threads. If there is no discrepancy or
only light corrosion, as defined in the service bulletin, the service
bulletin specifies repeating the inspection at a reduced inspection
interval. If there is any severe corrosion, or damaged or fretted
thread, the service bulletin specifies replacing the eye-end assembly
or affected hardware with a new or
[[Page 54940]]
serviceable part. If any discrepancy of the threads of the piston is
found, the service bulletin specifies returning the piston to the
manufacturer for repair.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The EASA mandated
the service information and issued airworthiness directive 2006-0139,
dated May 23, 2006, to ensure the continued airworthiness of these
airplanes in the European Union.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in the United Kingdom and
are type certificated for operation in the United States under the
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement. As
described in FAA Order 8100.14A, ``Interim Procedures for Working with
the European Community on Airworthiness Certification and Continued
Airworthiness,'' dated August 12, 2005, the EASA has kept the FAA
informed of the situation described above. We have examined the EASA's
findings, evaluated all pertinent information, and determined that we
need to issue an AD for products of this type design that are
certificated for operation in the United States.
Therefore, we are proposing this AD, which would require
determining the part number (P/N) of all six lift spoiler jacks, and,
for affected lift spoiler jacks, accomplishing the actions specified in
the service information described previously, except as discussed under
``Differences Between the Proposed AD and Service Information.''
Differences Between the Proposed AD and Service Information
If any discrepancy of the threads of the piston is found, the
service bulletin specifies returning the piston to the manufacturer for
repair. This proposed AD would not require this action. Instead, this
proposed AD would require replacing the piston with a new or
serviceable piston.
The service bulletin does not specify the type of inspection
necessary to find discrepancies of the eye-end assembly of the lift
spoiler jacks. We have determined that a detailed inspection is needed.
Note 1 of this proposed AD defines this type of inspection.
Costs of Compliance
This proposed AD would affect about 53 airplanes of U.S. registry.
The proposed inspections would take about 4 work hours per airplane,
per inspection cycle, at an average labor rate of $80 per work hour.
Based on these figures, the estimated cost of the proposed AD for U.S.
operators is $16,960, or $320 per airplane, per inspection cycle.
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 have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 that the proposed
regulation:
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 proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
BAE Systems (Operations) Limited (Formerly British Aerospace
Regional Aircraft): Docket No. FAA-2006-25851; Directorate
Identifier 2006-NM-133-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by October
20, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited
Model BAe 146-100A, -200A, and -300A series airplanes; and Model
Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in
any category.
Unsafe Condition
(d) This AD results from a report that a lift spoiler deployed
in flight due to corrosion at the thread where the eye-end assembly
was screwed into the piston of the lift spoiler actuator/jack
(referred to after this as the ``lift spoiler jack''). We are
issuing this AD to prevent detachment of the eye-end assembly of a
lift spoiler jack, which could result in uncommanded deployment of a
lift spoiler in flight, and consequent reduced controllability of
the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of BAE Systems (Operations) Limited
Inspection Service Bulletin SB27-176, Revision 2, dated October 5,
2004. Although the service bulletin specifies to submit information
to the manufacturer, this AD does not include that requirement.
Inspections and corrective actions accomplished before the effective
date of this AD in accordance with BAE Systems (Operations) Limited
Inspection Service Bulletin SB27-176, dated October 1, 2003; or
Revision 1, dated January 13, 2004; are acceptable for compliance
with the corresponding actions required by this AD.
Determination of Part Number (P/N)
(g) Within 30 days after the effective date of this AD:
Determine the P/N of all six lift
[[Page 54941]]
spoiler jacks. A review of airplane maintenance records is an
acceptable method of determining the P/N if the P/N can be
conclusively determined from that review.
(1) If no lift spoiler jack having P/N P308-45-0002 or P308-45-
0102 is installed: No further action is required by this paragraph.
(2) For any lift spoiler jack having P/N P308-45-0002 or P308-
45-0102: Before further flight, inspect the lift spoiler jack to
determine its serial number (S/N) and date of manufacture. A review
of airplane maintenance records is acceptable in lieu of this
inspection if the S/N and date of manufacture can be conclusively
determined from that review.
Inspection of Lift Spoiler Jack
(h) For any lift spoiler jack having P/N P308-45-0002 or P308-
45-0102: At the applicable compliance time specified in paragraph
(h)(1) or (h)(2) of this AD, perform a detailed inspection for
discrepancies of the eye-end assembly of the lift spoiler jack,
associated hardware, and the thread of the piston where the eye-end
assembly attaches, in accordance with the service bulletin.
Discrepancies include but are not limited to evidence of corrosion
or damaged or fretted threads.
(1) For lift spoiler jacks identified in paragraphs (h)(1)(i)
and (h)(1)(ii) of this AD: Within 30 days after the effective date
of this AD.
(i) Any lift spoiler jack having a S/N prefixed with ``DAWX'' or
``CSW'' (regardless of the date of manufacture).
(ii) Any lift spoiler jack having P/N P308-45-0002 or P308-45-
0102, with a date of manufacture on or before December 31, 1999.
(2) For lift spoiler jacks with a date of manufacture on or
after January 1, 2000, except those with S/Ns prefixed with ``DAWX''
or ``CSW'': Within 5 months after the effective date of this AD.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repetitive Inspections/Corrective Action
(i) Repeat the inspection required by paragraph (h) of this AD
and do corrective actions based on the inspection findings, in
accordance with paragraph (i)(1), (i)(2), or (i)(3) of this AD, as
applicable.
(1) If no discrepancy of the eye-end assembly of the lift
spoiler jack is found: Repeat the inspection required by paragraph
(h) of this AD within 48 months, and, based on the findings during
that repeat inspection, repeat the inspection and do corrective
actions, as applicable, in accordance with paragraph (i) of this AD.
(2) If light corrosion, as defined in the service bulletin, but
no other discrepancy, is found: Repeat the inspection required by
paragraph (h) of this AD within 24 months, and, based on the
findings during that repeat inspection, repeat the inspection and do
corrective actions, as applicable, in accordance with paragraph (i)
of this AD.
(3) If severe corrosion, as defined in the service bulletin, or
any damaged or fretted thread, is found: Before further flight,
replace the eye-end assembly of the lift spoiler jack, associated
hardware, and piston, as applicable, with new or serviceable parts,
as applicable, in accordance with the service bulletin. Then, repeat
the inspection required by paragraph (h) of this AD within 48
months, and, based on the findings during that repeat inspection,
repeat the inspection and do corrective actions, as applicable, in
accordance with paragraph (i) of this AD. Where the service bulletin
specifies to return certain damaged parts to the parts manufacturer,
this AD does not require that action.
Parts Installation
(j) As of the effective date of this AD, no person may install a
lift spoiler jack having P/N P308-45-0002 or P308-45-0102 unless it
has been inspected as required by this AD and found to be free of
severe corrosion or other discrepancy.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(l) The European Aviation Safety Agency's airworthiness
directive 2006-0139, dated May 23, 2006, also addresses the subject
of this AD.
Issued in Renton, Washington, on September 12, 2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-15592 Filed 9-19-06; 8:45 am]
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