Airworthiness Directives; British Aerospace Model HS 748 Airplanes, 70038-70041 [05-22790]
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Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Rules and Regulations
cycles on the thrust reverser since new or
within 6 months after the effective date of
this AD, whichever is later.
Note 2: Airbus Service Bulletin A340–78–
4028, Revision 01, dated October 23, 2003,
references Rohr Service Bulletin RA34078–
71, Revision 1, dated February 7, 2003, as an
additional source of service information for
accomplishing the applicable actions in
paragraph (f) of this AD.
(g) At the later of the times specified in
paragraphs (g)(1) and (g)(2) of this AD:
Accomplish an eddy current inspection for
cracking of the J-ring structure at the 12
o’clock and 6 o’clock positions by doing all
the applicable actions in accordance with
CFM International CFM56–5C Alert Service
Bulletin 78–A0072, Revision 2, dated January
27, 2004, including Rohr Alert Service
Bulletin RA340A78–72, Revision 2, dated
January 27, 2004. If no cracking is found:
Repeat the inspection thereafter at intervals
not to exceed 800 flight hours or 175 flight
cycles on the thrust reverser, whichever is
first.
(1) Before the accumulation of 3,000 total
flight cycles on any thrust reverser since
new.
(2) Within 800 flight hours or 175 flight
cycles after the effective date of this AD,
whichever is first.
(h) If any cracking is found at the 12
o’clock position, before further flight, do the
actions required by either paragraph (h)(1) or
(h)(2) of this AD.
(1) Replace the thrust reverser by doing all
the applicable actions in accordance with
CFM International CFM56–5C Alert Service
Bulletin 78–A0072, Revision 2, dated January
27, 2004, including Rohr Alert Service
Bulletin RA340A78–72, Revision 2, dated
January 27, 2004.
(2) Modify the J-ring and replace the 12
o’clock fitting by doing all the applicable
actions in accordance with CFM
International CFM56–5C Alert Service
Bulletin 78–A0073, Revision 1, dated January
27, 2004, including Rohr Alert Service
Bulletin RA340A78–73, Revision 1, dated
January 27, 2004. Except, if any cracking is
found on machined parts, repair the damage
using a method approved by the Manager,
International Branch, ANM–116. Repeat the
inspection of the 6 o’clock position only at
the time specified in paragraph (g) of this AD.
(i) If cracking is found at the 6 o’clock
position: Before further flight, replace the
thrust reverser by doing all the applicable
actions in accordance with CFM
International CFM56–5C Alert Service
Bulletin 78–A0072, Revision 2, dated January
27, 2004, including Rohr Alert Service
Bulletin RA340A78–72, Revision 2, dated
January 27, 2004.
No Reporting Required
(j) Although Airbus Service Bulletin A340–
78–4028, Revision 01, dated October 23,
2003; and CFM International CFM56–5C
Alert Service Bulletin 78–A0072, Revision 2,
dated January 27, 2004, specify reporting the
replacement of any thrust reverser to Airbus
or CFM, this AD does not include that
requirement.
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Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(k)(1) The Manager, International Branch,
ANM–116, 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 § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Federal Aviation Administration
(l) French airworthiness directives 2003–
108(B), dated March 19, 2003; and F–2004–
020, dated February 4, 2004, also address the
subject of this AD.
Material Incorporated by Reference
(m) You must use Airbus Service Bulletin
A340–78–4028, Revision 01, excluding
Appendix 01, dated October 23, 2003; CFM
International CFM56–5C Alert Service
Bulletin 78–A0072, Revision 2, dated January
27, 2004, including Rohr Alert Service
Bulletin RA340A78–72, Revision 2, dated
January 27, 2004; and CFM International
CFM56–5C Alert Service Bulletin 78–A0073,
Revision 1, dated January 27, 2004, including
Rohr Alert Service Bulletin RA340A78–73,
Revision 1, dated January 27, 2004; as
applicable; to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of these documents in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; or
Rohr Inc., 850 Lagoon Drive, Chula Vista,
California 91912, for a copy of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA).
For information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
November 9, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–22789 Filed 11–18–05; 8:45 am]
BILLING CODE 4910–13–P
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[Docket No. FAA–2005–23006; Directorate
Identifier 2002–NM–51–AD; Amendment 39–
14380; AD 2005–23–22]
RIN 2120–AA64
Airworthiness Directives; British
Aerospace Model HS 748 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
Related Information
PO 00000
14 CFR Part 39
Sfmt 4700
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
British Aerospace Model HS 748
airplanes. This AD requires repetitive
inspections for fatigue cracking,
corrosion, and other related
discrepancies of the rear pressure
bulkhead and associated areas, and the
fin attachment fittings, particularly the
fin link beam; and related investigative
and corrective actions. This AD results
from a structural integrity audit of the
airplane that showed the importance of
inspecting for fatigue cracking and
corrosion of these areas. We are issuing
this AD to detect and correct cracking,
corrosion, and other related
discrepancies of the rear pressure
bulkhead and associated areas, and the
fin attachment fittings, particularly the
fin link beam, which could result in
damage to the airplane structure or
injury to airplane occupants.
DATES: This AD becomes effective
December 6, 2005.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of December 6, 2005.
We must receive comments on this
AD by January 20, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://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,
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Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Rules and Regulations
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 AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1175;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Authority (CAA),
which is the airworthiness authority for
the United Kingdom, notified us that an
unsafe condition may exist on all British
Aerospace Model HS 748 airplanes. The
CAA advises that a structural integrity
audit of the airplane showed the
importance of inspecting for fatigue
cracking and corrosion of the rear
pressure bulkhead and associated areas,
and of the fin attachment fittings,
particularly the fin link beam. Although
there have been no reports of damage or
corrosion, the CAA has determined that
the potential exists for fatigue cracking
or corrosion to occur in these areas. The
CAA further advises that, in order to do
the inspection, operators must remove
the fin, and that other inspections for
cracking or corrosion and certain
replacements should be done while the
fin is removed. Failure to detect and
repair cracking, corrosion, and other
related discrepancies of the rear
pressure bulkhead and associated areas,
and the fin attachment fittings,
particularly the fin link beam, could
result in damage to the airplane
structure or injury to airplane
occupants.
Relevant Service Information
BAE Systems (Operations) Limited
has issued Inspection Service Bulletin
HS748–53–49, Revision 2, dated May 4,
2001. The service bulletin describes
procedures for doing various repetitive
inspections of the rear pressure
bulkhead and associated areas, and of
the fin attachment fittings, particularly
the fin link beam. The service bulletin
also states that, in order to inspect these
areas, the fin of the airplane must be
removed. The inspections include high
frequency eddy current (HFEC), rototest
eddy current, radiographic, and close
visual inspections for fatigue cracking
and corrosion, and for other related
discrepancies described in the service
bulletin, such as loose rivets, and worn
bolts and bushings.
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The service bulletin also describes
procedures for any necessary corrective
actions. The corrective actions depend
on the inspection findings and the
location of the problem to be corrected.
The corrective actions can include
reaming rivet holes, installing
appropriate new bolts, repairing cracks
and corrosion, and replacing various
parts with new or serviceable parts. The
corrective actions can also include
related investigative actions such as
close visual inspections for cracks,
corrosion, and discrepancies that may
be revealed during the repair process.
For certain inspection findings, such
as certain bore diameters or certain
cracks, and for certain areas that cannot
be repaired within the limits described
in the service bulletin, the service
bulletin specifies that operators should
contact BAE Systems (Operations)
Limited for repair instructions. The
service bulletin also specifies that
certain parts are to be returned to the
manufacturer, and that results of all
inspections should be sent to the
manufacturer.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. The CAA mandated the
service information and issued British
airworthiness directive 002–03–83 to
ensure the continued airworthiness of
these airplanes in the United Kingdom.
FAA’s Determination and Requirements
of This AD
This airplane model is manufactured
in the United Kingdom and is 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. Pursuant to this bilateral
airworthiness agreement, the CAA has
kept the FAA informed of the situation
described above. We have examined the
CAA’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 issuing this AD to
detect and correct cracking, corrosion,
and other related discrepancies of the
rear pressure bulkhead and associated
areas, and the fin attachment fittings,
particularly the fin link beam, which
could result in damage to the airplane
structure or injury to airplane
occupants. This AD requires
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Differences Among the AD, the British
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70039
Airworthiness Directive, and the Service
Bulletin.’’
Differences Among the AD, the British
Airworthiness Directive, and the
Service Bulletin
Although the service bulletin
referenced by the British airworthiness
directive specifies to submit certain
information to the manufacturer, and to
return certain parts to the manufacturer,
this AD does not include those
requirements.
The service bulletin referenced by the
British airworthiness directive specifies
to contact the manufacturer for
instructions on how to repair certain
conditions, but this AD requires
repairing those conditions using a
method that we approve.
Clarification of Actions in the Service
Bulletin
Where the service bulletin is not
specific regarding an inspection,
corrective action, or any step necessary
to complete the requirements of this AD,
this AD requires doing the applicable
action or step using a method that we,
or the CAA (or its delegated agent)
approve.
Clarification of Inspection Terminology
In this AD, the ‘‘close visual
inspection’’ specified in the service
bulletin is referred to as a ‘‘detailed
inspection.’’ We have included the
definition for a detailed inspection in a
note in the AD.
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
If an affected airplane is imported and
placed on the U.S. Register in the future,
the required actions would take about
200 work hours per airplane, at an
average labor rate of $65 per work hour.
Based on these figures, the estimated
cost of the AD would be $13,000 per
airplane, per inspection cycle.
FAA’s Determination of the Effective
Date
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
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70040
Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Rules and Regulations
less than 30 days after it is published in
the Federal Register.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2005–23006; Directorate Identifier
2002–NM–51–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
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 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
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://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.
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
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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.
Effective Date
Regulatory Findings
We have 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 that the 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 AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
Unsafe Condition
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2005–23–22 BAE Systems (Operations)
Limited (Formerly British Aerospace
Regional Aircraft): Amendment 39–
14380. Docket No. FAA–2005–23006;
Directorate Identifier 2002–NM–51–AD.
PO 00000
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(a) This AD becomes effective December 6,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems
(Operations) Limited Model HS 748 series 2A
and series 2B airplanes, certificated in any
category.
(d) This AD results from a structural
integrity audit of the airplane that showed
the importance of inspecting for fatigue
cracking and corrosion of the rear pressure
bulkhead and associated areas, and of the fin
attachment fittings, particularly the fin link
beam. We are issuing this AD to detect and
correct cracking, corrosion, and other related
discrepancies of these areas, which could
result in damage to the airplane structure or
injury to airplane occupants.
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.
Inspections and Corrective Actions
(f) At the applicable time in paragraph
(f)(1), (f)(2), or (f)(3) of this AD: Do high
frequency eddy current (HFEC), rototest eddy
current, radiographic, and detailed
inspections for fatigue cracking, corrosion,
and other related discrepancies of the rear
pressure bulkhead and associated areas, and
the fin attachment fittings, particularly the
fin link beam; and do applicable related
investigative and corrective actions before
further flight except as provided by
paragraph (g) of this AD. Do all actions in
accordance with the Accomplishment
Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin HS748–
53–49, Revision 2, dated May 4, 2001.
(1) For airplanes with maximum cabin
differential pressure of 5.5 psi, do the
inspections at the applicable time in
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(i) Before the accumulation of 50,000 total
flight cycles, or within 6 months after the
effective date of this AD, whichever occurs
later.
(ii) Before the accumulation of 83,000 total
flight cycles, or within 6 months after the
effective date of this AD, whichever occurs
later: Extend the inspection of the fin link
beam to cover the central 30 inches of the
beam, and repeat this inspection at intervals
not to exceed 11,000 flight cycles. If the
inspection of the fin link beam indicates a
defect in any rivet hole, before further flight:
Repair the hole in accordance with the
service bulletin, and repeat the inspection
thereafter at intervals not to exceed the
applicable interval in Table 1 of this AD,
depending on the size of the hole following
reaming during the repair process.
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70041
TABLE 1.—REPETITIVE INTERVALS FOR AIRPLANES WITH REPAIRED RIVET HOLES, MAXIMUM CABIN DIFFERENTIAL
PRESSURE 5.5 PSI
Repetitive inspection
interval
Defect removed at—
Hole size 3/16 inch + 1/32 inch diameter ......................................................................................................................
Hole size 3/16 inch + 1/16 inch diameter ......................................................................................................................
Hole size 3/16 inch + 5/64 inch diameter ......................................................................................................................
(2) For airplanes on which BAe
Modification 7191 has been incorporated
(reduction of cabin differential pressure from
5.5 psi to 4.2 psi) before the effective date of
this AD: Do the inspections at the applicable
time in paragraphs (f)(2)(i), (f)(2)(ii), and
(f)(2)(iii) of this AD.
(i) If Modification 7191 is incorporated
before the accumulation of 50,000 total flight
cycles, do the inspections before the
accumulation of 50,000 total flight cycles, or
within 6 months after the effective date of
this AD, whichever occurs later. Repeat the
inspection thereafter at intervals not to
exceed 25,000 flight cycles.
(ii) If Modification 7191 is incorporated
during one of the inspections required by this
AD: Repeat the inspection thereafter at
intervals not to exceed 25,000 flight cycles.
(iii) If Modification 7191 is incorporated
between inspections required by this AD: Do
the inspection 11,000 flight cycles following
10,000 flight cycles.
7,000 flight cycles.
6,000 flight cycles.
the previous inspection, and repeat the
inspection thereafter at intervals not to
exceed 25,000 flight cycles. If the inspection
of the fin link beam indicates a defect in any
rivet hole, before further flight: Repair the
hole in accordance with the service bulletin,
and repeat the inspection thereafter at
intervals not to exceed the applicable interval
in Table 2 of this AD, depending on the size
of the hole following reaming during the
repair process.
TABLE 2.—REPETITIVE INTERVALS FOR AIRPLANES WITH REPAIRED RIVET HOLES, MAXIMUM CABIN DIFFERENTIAL
PRESSURE 4.2 PSI
Repetitive inspection
interval
Defect removed at—
Hole size 3/16 inch + 1/32 inch diameter ......................................................................................................................
Hole size 3/16 inch + 1/16 inch diameter ......................................................................................................................
Hole size 3/16 inch + 5/64 inch diameter ......................................................................................................................
(3) For series 1 airplanes, including Model
200, Constructors Number 1535 (maximum
cabin differential pressure of 4.2 psi): Before
the accumulation of 70,000 total flight cycles,
or within 6 months after the effective date of
this AD, whichever occurs later. If the
inspection of the fin link beam indicates a
defect in any rivet hole, before further flight:
Repair the hole in accordance with the
service bulletin, and repeat the inspection
thereafter at intervals not to exceed the
applicable interval in Table 2 of this AD,
depending on the size of the hole following
reaming during the repair process.
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.’’
(g) Where BAE Systems (Operations)
Limited Inspection Service Bulletin HS748–
53–49, Revision 2, dated May 4, 2001,
recommends contacting BAE Systems
(Operations) Limited for appropriate action:
Before further flight, do the action according
to a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA. Where the service
bulletin is not specific regarding an
inspection, corrective action, or any step
necessary to complete the requirements of
this AD: Before further flight, do the
inspection, corrective action, or step
according to a method approved by the
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Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA, or by
the CAA (or its delegated agent).
No Reporting Required
(h) Although the service bulletin
referenced in this AD specifies to submit
certain information to the manufacturer, this
AD does not include that requirement.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, International Branch,
ANM–116, 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 § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
service information. You may review copies
at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
November 9, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–22790 Filed 11–18–05; 8:45 am]
BILLING CODE 4910–13–P
Related Information
(j) British airworthiness directive 002–03–
83 also addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use BAE Systems
(Operations) Limited Inspection Service
Bulletin HS748–53–49, Revision 2, dated
May 4, 2001, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact British Aerospace Regional Aircraft
American Support 13850 Mclearen Road,
Herndon, Virginia 20171, for a copy of this
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22,000 flight cycles.
16,000 flight cycles.
14,000 flight cycles.
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]]>Agencies
[Federal Register Volume 70, Number 223 (Monday, November 21, 2005)]
[Rules and Regulations]
[Pages 70038-70041]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-22790]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23006; Directorate Identifier 2002-NM-51-AD;
Amendment 39-14380; AD 2005-23-22]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Model HS 748
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
British Aerospace Model HS 748 airplanes. This AD requires repetitive
inspections for fatigue cracking, corrosion, and other related
discrepancies of the rear pressure bulkhead and associated areas, and
the fin attachment fittings, particularly the fin link beam; and
related investigative and corrective actions. This AD results from a
structural integrity audit of the airplane that showed the importance
of inspecting for fatigue cracking and corrosion of these areas. We are
issuing this AD to detect and correct cracking, corrosion, and other
related discrepancies of the rear pressure bulkhead and associated
areas, and the fin attachment fittings, particularly the fin link beam,
which could result in damage to the airplane structure or injury to
airplane occupants.
DATES: This AD becomes effective December 6, 2005.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 6,
2005.
We must receive comments on this AD by January 20, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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,
[[Page 70039]]
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 AD.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, notified us that an unsafe condition
may exist on all British Aerospace Model HS 748 airplanes. The CAA
advises that a structural integrity audit of the airplane showed the
importance of inspecting for fatigue cracking and corrosion of the rear
pressure bulkhead and associated areas, and of the fin attachment
fittings, particularly the fin link beam. Although there have been no
reports of damage or corrosion, the CAA has determined that the
potential exists for fatigue cracking or corrosion to occur in these
areas. The CAA further advises that, in order to do the inspection,
operators must remove the fin, and that other inspections for cracking
or corrosion and certain replacements should be done while the fin is
removed. Failure to detect and repair cracking, corrosion, and other
related discrepancies of the rear pressure bulkhead and associated
areas, and the fin attachment fittings, particularly the fin link beam,
could result in damage to the airplane structure or injury to airplane
occupants.
Relevant Service Information
BAE Systems (Operations) Limited has issued Inspection Service
Bulletin HS748-53-49, Revision 2, dated May 4, 2001. The service
bulletin describes procedures for doing various repetitive inspections
of the rear pressure bulkhead and associated areas, and of the fin
attachment fittings, particularly the fin link beam. The service
bulletin also states that, in order to inspect these areas, the fin of
the airplane must be removed. The inspections include high frequency
eddy current (HFEC), rototest eddy current, radiographic, and close
visual inspections for fatigue cracking and corrosion, and for other
related discrepancies described in the service bulletin, such as loose
rivets, and worn bolts and bushings.
The service bulletin also describes procedures for any necessary
corrective actions. The corrective actions depend on the inspection
findings and the location of the problem to be corrected. The
corrective actions can include reaming rivet holes, installing
appropriate new bolts, repairing cracks and corrosion, and replacing
various parts with new or serviceable parts. The corrective actions can
also include related investigative actions such as close visual
inspections for cracks, corrosion, and discrepancies that may be
revealed during the repair process.
For certain inspection findings, such as certain bore diameters or
certain cracks, and for certain areas that cannot be repaired within
the limits described in the service bulletin, the service bulletin
specifies that operators should contact BAE Systems (Operations)
Limited for repair instructions. The service bulletin also specifies
that certain parts are to be returned to the manufacturer, and that
results of all inspections should be sent to the manufacturer.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The CAA mandated
the service information and issued British airworthiness directive 002-
03-83 to ensure the continued airworthiness of these airplanes in the
United Kingdom.
FAA's Determination and Requirements of This AD
This airplane model is manufactured in the United Kingdom and is
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. Pursuant
to this bilateral airworthiness agreement, the CAA has kept the FAA
informed of the situation described above. We have examined the CAA'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 issuing this AD to detect and correct cracking,
corrosion, and other related discrepancies of the rear pressure
bulkhead and associated areas, and the fin attachment fittings,
particularly the fin link beam, which could result in damage to the
airplane structure or injury to airplane occupants. This AD requires
accomplishing the actions specified in the service information
described previously, except as discussed under ``Differences Among the
AD, the British Airworthiness Directive, and the Service Bulletin.''
Differences Among the AD, the British Airworthiness Directive, and the
Service Bulletin
Although the service bulletin referenced by the British
airworthiness directive specifies to submit certain information to the
manufacturer, and to return certain parts to the manufacturer, this AD
does not include those requirements.
The service bulletin referenced by the British airworthiness
directive specifies to contact the manufacturer for instructions on how
to repair certain conditions, but this AD requires repairing those
conditions using a method that we approve.
Clarification of Actions in the Service Bulletin
Where the service bulletin is not specific regarding an inspection,
corrective action, or any step necessary to complete the requirements
of this AD, this AD requires doing the applicable action or step using
a method that we, or the CAA (or its delegated agent) approve.
Clarification of Inspection Terminology
In this AD, the ``close visual inspection'' specified in the
service bulletin is referred to as a ``detailed inspection.'' We have
included the definition for a detailed inspection in a note in the AD.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
If an affected airplane is imported and placed on the U.S. Register
in the future, the required actions would take about 200 work hours per
airplane, at an average labor rate of $65 per work hour. Based on these
figures, the estimated cost of the AD would be $13,000 per airplane,
per inspection cycle.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in
[[Page 70040]]
less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2005-
23006; Directorate Identifier 2002-NM-51-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
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 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
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
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.
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 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 that the 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 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, 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2005-23-22 BAE Systems (Operations) Limited (Formerly British
Aerospace Regional Aircraft): Amendment 39-14380. Docket No. FAA-
2005-23006; Directorate Identifier 2002-NM-51-AD.
Effective Date
(a) This AD becomes effective December 6, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited
Model HS 748 series 2A and series 2B airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from a structural integrity audit of the
airplane that showed the importance of inspecting for fatigue
cracking and corrosion of the rear pressure bulkhead and associated
areas, and of the fin attachment fittings, particularly the fin link
beam. We are issuing this AD to detect and correct cracking,
corrosion, and other related discrepancies of these areas, which
could result in damage to the airplane structure or injury to
airplane occupants.
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.
Inspections and Corrective Actions
(f) At the applicable time in paragraph (f)(1), (f)(2), or
(f)(3) of this AD: Do high frequency eddy current (HFEC), rototest
eddy current, radiographic, and detailed inspections for fatigue
cracking, corrosion, and other related discrepancies of the rear
pressure bulkhead and associated areas, and the fin attachment
fittings, particularly the fin link beam; and do applicable related
investigative and corrective actions before further flight except as
provided by paragraph (g) of this AD. Do all actions in accordance
with the Accomplishment Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin HS748-53-49, Revision 2, dated
May 4, 2001.
(1) For airplanes with maximum cabin differential pressure of
5.5 psi, do the inspections at the applicable time in paragraphs
(f)(1)(i) and (f)(1)(ii) of this AD.
(i) Before the accumulation of 50,000 total flight cycles, or
within 6 months after the effective date of this AD, whichever
occurs later.
(ii) Before the accumulation of 83,000 total flight cycles, or
within 6 months after the effective date of this AD, whichever
occurs later: Extend the inspection of the fin link beam to cover
the central 30 inches of the beam, and repeat this inspection at
intervals not to exceed 11,000 flight cycles. If the inspection of
the fin link beam indicates a defect in any rivet hole, before
further flight: Repair the hole in accordance with the service
bulletin, and repeat the inspection thereafter at intervals not to
exceed the applicable interval in Table 1 of this AD, depending on
the size of the hole following reaming during the repair process.
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Table 1.--Repetitive Intervals for Airplanes With Repaired Rivet Holes,
Maximum Cabin Differential Pressure 5.5 psi
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Defect removed at-- Repetitive inspection interval
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Hole size 3/16 inch + 1/32 inch 10,000 flight cycles.
diameter.
Hole size 3/16 inch + 1/16 inch 7,000 flight cycles.
diameter.
Hole size 3/16 inch + 5/64 inch 6,000 flight cycles.
diameter.
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(2) For airplanes on which BAe Modification 7191 has been
incorporated (reduction of cabin differential pressure from 5.5 psi
to 4.2 psi) before the effective date of this AD: Do the inspections
at the applicable time in paragraphs (f)(2)(i), (f)(2)(ii), and
(f)(2)(iii) of this AD.
(i) If Modification 7191 is incorporated before the accumulation
of 50,000 total flight cycles, do the inspections before the
accumulation of 50,000 total flight cycles, or within 6 months after
the effective date of this AD, whichever occurs later. Repeat the
inspection thereafter at intervals not to exceed 25,000 flight
cycles.
(ii) If Modification 7191 is incorporated during one of the
inspections required by this AD: Repeat the inspection thereafter at
intervals not to exceed 25,000 flight cycles.
(iii) If Modification 7191 is incorporated between inspections
required by this AD: Do the inspection 11,000 flight cycles
following the previous inspection, and repeat the inspection
thereafter at intervals not to exceed 25,000 flight cycles. If the
inspection of the fin link beam indicates a defect in any rivet
hole, before further flight: Repair the hole in accordance with the
service bulletin, and repeat the inspection thereafter at intervals
not to exceed the applicable interval in Table 2 of this AD,
depending on the size of the hole following reaming during the
repair process.
Table 2.--Repetitive Intervals for Airplanes With Repaired Rivet Holes,
Maximum Cabin Differential Pressure 4.2 psi
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Defect removed at-- Repetitive inspection interval
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Hole size 3/16 inch + 1/32 inch 22,000 flight cycles.
diameter.
Hole size 3/16 inch + 1/16 inch 16,000 flight cycles.
diameter.
Hole size 3/16 inch + 5/64 inch 14,000 flight cycles.
diameter.
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(3) For series 1 airplanes, including Model 200, Constructors
Number 1535 (maximum cabin differential pressure of 4.2 psi): Before
the accumulation of 70,000 total flight cycles, or within 6 months
after the effective date of this AD, whichever occurs later. If the
inspection of the fin link beam indicates a defect in any rivet
hole, before further flight: Repair the hole in accordance with the
service bulletin, and repeat the inspection thereafter at intervals
not to exceed the applicable interval in Table 2 of this AD,
depending on the size of the hole following reaming during the
repair process.
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.''
(g) Where BAE Systems (Operations) Limited Inspection Service
Bulletin HS748-53-49, Revision 2, dated May 4, 2001, recommends
contacting BAE Systems (Operations) Limited for appropriate action:
Before further flight, do the action according to a method approved
by the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA. Where the service bulletin is not specific
regarding an inspection, corrective action, or any step necessary to
complete the requirements of this AD: Before further flight, do the
inspection, corrective action, or step according to a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, or by the CAA (or its delegated agent).
No Reporting Required
(h) Although the service bulletin referenced in this AD
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, International Branch, ANM-116, 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
(j) British airworthiness directive 002-03-83 also addresses the
subject of this AD.
Material Incorporated by Reference
(k) You must use BAE Systems (Operations) Limited Inspection
Service Bulletin HS748-53-49, Revision 2, dated May 4, 2001, to
perform the actions that are required by this AD, unless the AD
specifies otherwise. The Director of the Federal Register approved
the incorporation by reference of this document in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. Contact British Aerospace Regional
Aircraft American Support 13850 Mclearen Road, Herndon, Virginia
20171, for a copy of this service information. You may review copies
at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on November 9, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-22790 Filed 11-18-05; 8:45 am]
BILLING CODE 4910-13-P
