Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR Series Airplanes, 33595-33598 [06-5207]
Download as PDF
33595
Rules and Regulations
Federal Register
Vol. 71, No. 112
Monday, June 12, 2006
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24102; Directorate
Identifier 2005–NM–244–AD; Amendment
39–14638; AD 2006–12–12]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–300,
747–400, 747–400D, and 747SR Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
sroberts on PROD1PC70 with RULES
Examining the Docket
The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
747–100 and –200 series airplanes. That
AD currently requires repetitive
inspections for cracking of the station
800 frame assembly, and repair if
necessary. This new AD retains the
repetitive inspection requirements of
the existing AD, but expands the area to
be inspected. This AD also reduces the
initial inspection threshold, removes the
adjustment of the compliance threshold
and repetitive interval based on cabin
differential pressure, and adds airplanes
to the applicability. This AD results
from several reports of cracks of the
station 800 frame assembly on airplanes
that had accumulated fewer total flight
cycles than the initial inspection
threshold in the existing AD. We are
issuing this AD to detect and correct
fatigue cracks that could extend and
fully sever the frame, which could result
in development of skin cracks that
could lead to rapid depressurization of
the airplane.
DATES: This AD becomes effective July
17, 2006.
SUMMARY:
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18:28 Jun 09, 2006
Jkt 208001
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of July 17, 2006.
On August 30, 2001 (66 FR 38891,
July 26, 2001), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin 747–53A2451,
including Appendix A, dated October 5,
2000.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6437;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
You may examine the airworthiness
directive (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 street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2001–14–22, amendment
39–12333 (66 FR 38891, July 26, 2001).
The existing AD applies to certain
Boeing Model 747–100 and –200 series
airplanes. That NPRM was published in
the Federal Register on March 8, 2006
(71 FR 11551). That NPRM proposed to
require repetitive inspections for
cracking of the station 800 frame
assembly, and repair if necessary.
Comments
We provided the public the
opportunity to participate in the
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Sfmt 4700
development of this AD. We have
considered the comments that have
been received on the NPRM.
Support for the Proposed AD
Air Transport Association (ATA), on
behalf of its member Northwest
Airlines, concurs with the intent of the
NPRM.
Requests To Remove or Revise 12Month Grace Period From Table 2
Boeing requests that we remove the
12-month compliance time from
paragraph (h), Table 2, items (2) and (3),
of the NPRM. Boeing states that the
cracking that is the subject of the NPRM
is initiated and propagated solely by
cyclic loading as measured in flight
cycles. Boeing also states that calendar
time has no bearing on the initiation
rate of the cracking. ATA, on behalf of
Northwest Airlines, also comments on
the 12-month grace period. Northwest
states that, for operators who have
planned completion of the initial
inspection near the previously defined
19,000 flight-cycle threshold in
accordance with AD 2001–14–22, the
proposed 12-month grace period could
result in unscheduled out-of-service
airplanes. Northwest adds that the
cracking addressed by the NPRM is
attributed to fatigue, which is driven by
flight cycles rather than calendar days.
Northwest therefore requests that we
change the calendar time from 12
months to 18 months, which is
consistent with the Boeing maintenance
interval on Model 747 airplanes.
Northwest suggests limiting this
calendar-time change to airplanes that
have not exceeded the previously
mandated 19,000 total-flight-cycle
threshold. ATA states that this change
would avoid disruption of maintenance
visits that were scheduled to facilitate
compliance with the existing AD.
We agree that a grace period based on
calendar time is inappropriate because,
as Boeing states and ATA notes, the
cracking that is the subject of the NPRM
is initiated and propagated solely by
cyclic loading as measured in flight
cycles. For this reason, we disagree with
ATA’s request to extend the grace
period to 18 months for certain
airplanes. Instead, we have revised
Table 2 of the final rule to remove the
12-month portion of the grace period,
and to include only the compliance time
based on flight cycles. This change will
ensure an equivalent level of safety and
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Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Rules and Regulations
alleviate concerns about unscheduled
out-of-service airplanes.
Request To Clarify Expanded
Inspection Requirements for Previously
Inspected Airplanes
ATA, on behalf of Northwest Airlines,
also requests that, for airplanes on
which the inspections in accordance
with AD 2001–14–22 have been done,
we clarify that the inspection per
procedures defined in Boeing Alert
Service Bulletin 747–53A2451, Revision
1, dated November 10, 2005, be
accomplished at the next scheduled
repeat inspection. Northwest states that
this request complies with the statement
in the service bulletin that specifies no
additional work is necessary on
airplanes previously inspected in
accordance with the initial release of the
service bulletin (dated October 5, 2000),
and to do the expanded inspection at
the time of the next scheduled
inspection.
We partially agree. We agree with the
commenter that, for the previously
accomplished inspections, compliance
with AD 2001–14–22 was met if the
inspection was accomplished in
accordance with the original release of
the service bulletin (Boeing Alert
Service Bulletin 747–53A2451,
including Appendix A, dated October 5,
2000). It is the intent of the NPRM to
match the service information provided
by Boeing. We disagree that any change
is necessary to clarify the AD. Paragraph
(f) of the AD states that, prior to the
effective date of this new AD, the
inspections may be accomplished in
accordance with either the initial
release or Revision 1 of the service
bulletin. After the effective date of this
AD, only Revision 1 may be used. We
have not changed the AD in this regard.
sroberts on PROD1PC70 with RULES
Explanation of Change to Costs of
Compliance
After the NPRM was issued, we
reviewed the figures we have used over
the past several years to calculate AD
costs to operators. To account for
various inflationary costs in the airline
industry, we find it necessary to
increase the labor rate used in these
calculations from $65 per work hour to
$80 per work hour. The cost impact
information, below, reflects this
increase in the specified hourly labor
rate.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been received, and determined
that air safety and the public interest
require adopting the AD with the
changes described previously. We have
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18:28 Jun 09, 2006
Jkt 208001
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
Costs of Compliance
There are about 900 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 156 airplanes
of U.S. registry.
The inspections that are specified in
AD 2001–14–22, and retained in this
AD, take between 12 and 14 work hours
per airplane, depending on the airplane
configuration. The average labor rate is
$80 per work hour. Based on these
figures, the estimated cost of the
currently required actions is between
$960 and $1,120 per airplane, per
inspection cycle.
The new actions will take between 18
and 20 work hours per airplane, at an
average labor rate of $80 per work hour.
Based on these figures, the estimated
cost of the new actions specified in this
AD for U.S. operators is between
$224,640 and $249,600, or between
$1,440 and $1,600 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 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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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Frm 00002
Fmt 4700
Sfmt 4700
(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.
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
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 removing amendment 39–12333 (66
FR 38891, July 26, 2001) and by adding
the following new airworthiness
directive (AD):
I
2006–12–12 Boeing: Amendment 39–14638.
Docket No. FAA–2006–24102;
Directorate Identifier 2005–NM–244–AD.
Effective Date
(a) This AD becomes effective July 17,
2006.
Affected ADs
(b) This AD supersedes AD 2001–14–22.
Applicability
(c) This AD applies to all Boeing Model
747–100, 747–100B, 747–100B SUD, 747–
200B, 747–200C, 747–300, 747–400, 747–
400D, and 747SR series airplanes, certificated
in any category.
Unsafe Condition
(d) This AD results from several reports of
cracks of the station 800 frame assembly on
airplanes that had accumulated fewer total
flight cycles than the initial inspection
threshold in the existing AD. We are issuing
this AD to detect and correct fatigue cracks
that could extend and fully sever the frame,
which could result in development of skin
cracks that could lead to rapid
depressurization of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
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Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Rules and Regulations
the compliance times specified, unless the
actions have already been done.
Restatement of the Requirements of AD
2001–14–22
Repetitive Inspections
(f) For Boeing Model 747–100, 747–100B,
747–100B SUD, –200B, 747–200C, and 747–
200F series airplanes, as identified in Boeing
Alert Service Bulletin 747–53A2451,
including Appendix A, dated October 5,
2000: Do detailed, surface high-frequency
eddy current (HFEC), and open-hole HFEC
inspections, as applicable, for cracking of the
station 800 frame assembly (including the
inner chord strap, angles, and exposed web)
between stringers 14 and 18, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–53A2451,
including Appendix A, dated October 5,
2000; or Boeing Alert Service Bulletin 747–
33597
53A2451, Revision 1, dated November 10,
2005; after the effective date of this AD, only
Revision 1 of the service bulletin may be
used. Except as provided by paragraph (g) of
this AD, do the inspection at the applicable
time specified in Table 1 of this AD, and
repeat the inspections thereafter at intervals
not to exceed 3,000 flight cycles until the
initial inspections required by paragraph (h)
of this AD are accomplished.
TABLE 1.—COMPLIANCE TIMES
Total flight cycles as of August 30, 2001 (the effective date of AD 2001–14–22)
Do the inspection in paragraph (f) of this AD at this time
(1) Fewer than 19,000 ........................................
Before the accumulation of 19,000 total flight cycles, or within 1,500 flight cycles after August
30, 2001, whichever comes later.
Within 1,500 flight cycles or 12 months after August 30, 2001, whichever comes first.
Within 750 flight cycles or 12 months after August 30, 2001, whichever comes first.
(2) 19,000 or more, but 21,250 or fewer ............
(3) 21,251 or more ..............................................
Adjustments to Compliance Time: Cabin
Differential Pressure
(g) For Boeing Model 747–100, 747–100B,
747–100B SUD, –200B, 747–200C, and 747–
200F series airplanes, as identified in Boeing
Alert Service Bulletin 747–53A2451,
including Appendix A, dated October 5,
2000, that are inspected before the effective
date of this AD: Except as provided by
paragraph (i) of this AD, for the purposes of
calculating the compliance threshold and
repetitive interval for the actions required by
paragraph (f) of this AD, the number of flight
cycles in which cabin differential pressure is
at 2.0 pounds per square inch (psi) or less
need not be counted when determining the
number of flight cycles that have occurred on
the airplane, provided that the flight cycles
with momentary spikes in cabin differential
pressure above 2.0 psi are included as full
pressure cycles. For this provision to apply,
all cabin pressure records must be
maintained for each airplane: No fleetaveraging of cabin pressure is allowed.
New Requirements of this AD
Repetitive Inspections of Expanded Area at a
New Reduced Threshold
(h) For all airplanes, at the applicable time
specified in Table 2 of this AD, except as
provided by paragraph (i) of this AD, do the
following inspections of the station 800
frame assembly in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2451, Revision 1,
dated November 10, 2005: A detailed
inspection for cracking of the inner chord
strap, angles, and exposed web adjacent to
the inner chords on the station 800 frame
between stringer 14 and stringer 18; and
surface HFEC and open-hole HFEC
inspections for cracking of the inner chord
strap and angles. Do the initial inspections at
the applicable time specified in Table 2 of
this AD, and repeat the inspections thereafter
at intervals not to exceed 3,000 flight cycles.
Accomplishing the initial inspections
required by this paragraph terminates the
inspection requirements of paragraph (f) of
this AD.
TABLE 2.—REVISED COMPLIANCE TIMES
Total flight cycles as of the effective date
of this AD
Do the inspections in paragraph (h) of this AD at this time
(1) Fewer than 16,000 .............................
Before the accumulation of 16,000 total flight cycles, or within 1,500 flight cycles after the effective
date of this AD, whichever comes later.
Within 1,500 flight cycles after the effective date of this AD.
Within 750 flight cycles after the effective date of this AD.
sroberts on PROD1PC70 with RULES
(2) 16,000 or more, but 24,250 or fewer
(3) 24,251 or more ...................................
Adjustments to Compliance Time: Cabin
Differential Pressure
(i) For the purposes of calculating the
compliance threshold and repetitive interval
for actions required by paragraphs (f) and (h)
of this AD, on or after the effective date of
this AD: All flight cycles, including the
number of flight cycles in which cabin
differential pressure is at 2.0 psi or less, must
be counted when determining the number of
flight cycles that have occurred on the
airplane. However, for airplanes on which
the repetitive interval for the actions required
by paragraph (f) of this AD have been
calculated in accordance with paragraph (g)
of this AD by excluding the number of flight
cycles in which cabin differential pressure is
at 2.0 pounds psi or less: Continue to adjust
the repetitive inspection interval in
accordance with paragraph (g) of this AD
until the initial inspections required by
paragraph (h) of this AD are accomplished.
Thereafter, no adjustment to compliance
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18:28 Jun 09, 2006
Jkt 208001
times based on paragraph (g) of this AD is
allowed.
Repair
(j) If any cracking is detected during any
inspection required by paragraph (f) or (h) of
this AD, and the service bulletin specifies to
contact Boeing for appropriate action: Before
further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (l) of this AD.
No Report Required
(k) Although the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2451, including Appendix A, dated
October 5, 2000; and Boeing Alert Service
Bulletin 747–53A2451, Revision 1, dated
November 10, 2005; describe procedures for
reporting certain information to the
manufacturer, this AD does not require that
report.
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Sfmt 4700
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane.
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Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Rules and Regulations
(4) AMOCs approved previously in
accordance with AD 2001–14–22, are
approved as AMOCs for the corresponding
provisions of paragraphs (f) and (j) of this
AD.
Material Incorporated by Reference
(m) You must use Boeing Alert Service
Bulletin 747–53A2451, including Appendix
A, dated October 5, 2000; or Boeing Alert
Service Bulletin 747–53A2451, Revision 1,
dated November 10, 2005; as applicable; to
perform the actions that are required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 747–53A2451,
Revision 1, dated November 10, 2005, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On August 30, 2001 (66 FR 38891, July
26, 2001), the Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 747–53A2451,
including Appendix A, dated October 5,
2000.
(3) Contact Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington 98124–
2207, 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 May 31,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5207 Filed 6–9–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Examining the Docket
14 CFR Part 39
[Docket No. FAA–2006–24807; Directorate
Identifier 2005–SW–41–AD; Amendment 39–
14603; AD 2006–10–19]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Model EC130 B4 Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule; request for
comments.
sroberts on PROD1PC70 with RULES
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model
EC130 B4 helicopters. This action
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18:28 Jun 09, 2006
Jkt 208001
requires inspecting the throttle twist
grip (twist grip) assembly for any foreign
body (chip or debris), any rotating
micro-switch, and any micro-switch
roller that does not move freely. If any
unairworthy condition is found, this
action requires that it be corrected
before further flight. This amendment is
prompted by two reports of a twist grip
assembly jamming in the ‘‘IDLE’’
position. The actions specified in this
AD are intended to detect and prevent
jamming of the twist grip assembly,
which, if present, could keep the engine
from operating above idle speed and
result in subsequent loss of control of
the engine power of the helicopter.
DATES: Effective July 27, 2006.
Comments for inclusion in the Rules
Docket must be received on or before
August 11, 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; or
• 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.
You may get the service information
identified in this AD from American
Eurocopter Corporation, 2701 Forum
Drive, Grand Prairie, Texas 75053–4005,
telephone (972) 641–3460, fax (972)
641–3527.
You may examine the docket that
contains the AD, any comments, and
other information on the Internet at
https://dms.dot.gov, or in person at the
Docket Management System (DMS)
Docket Offices between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket Office
(telephone (800) 647–5227) is located on
the plaza level of the Department of
Transportation Nassif Building at the
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
FOR FURTHER INFORMATION CONTACT: Ed
Cuevas, Aviation Safety Engineer, FAA,
Rotorcraft Directorate, Safety
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Frm 00004
Fmt 4700
Sfmt 4700
Management Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5355,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION: This
amendment adopts a new AD for
Eurocopter Model EC130 B4 helicopters.
This action requires, within 30 hours
time-in-service (TIS), unless
accomplished during the previous 100hour TIS or annual inspection,
inspecting the twist grip assembly for
any foreign body (chip or debris), any
rotating micro-switch, and any microswitch roller that does not move freely.
If any unairworthy condition is found,
this action requires that it be corrected
before further flight. This amendment is
prompted by reports of two incidents in
which a twist grip assembly jammed in
the ‘‘IDLE’’ position. Analyses
conducted by the manufacturer revealed
that a chip was caught between the
roller of the ‘‘FLIGHT’’ micro-switch
and the cam in one of the reported
incidents, and marks on the cam
indicated that debris had been present
in the second incident. This condition,
if not detected, could result in jamming
of the twist grip assembly, which, if
present, could keep the engine from
operating above idle speed and result in
subsequent loss of control of the engine
power of the helicopter.
The Direction Generale de L’Aviation
Civile (DGAC), the airworthiness
authority for France, notified the FAA
that an unsafe condition may exist on
Eurocopter Model EC130 B4 helicopters
before embodiment of MOD 073773
fitted with a twist grip assembly, part
number (P/N) 350A27–5209–00, P/N
350A27–5209–01, or P/N 350A27–
5209–02, installed. The DGAC advises
of two reports of twist grip assembly
jamming in the ‘‘IDLE’’ position.
Eurocopter has issued Alert Telex No.
05A003, dated June 30, 2005, which
specifies an initial and repetitive
functional checks of the twist grip
assembly on Model EC130 B4
helicopters. The DGAC classified this
alert telex as mandatory and issued AD
No. F–2005–145, dated August 17, 2005,
to ensure the continued airworthiness of
these helicopters in France.
This helicopter model is
manufactured in France and is type
certificated for operation in the United
States under the provisions of 14 CFR
21.29 and the applicable bilateral
agreement. Pursuant to the applicable
bilateral agreement, the DGAC has kept
the FAA informed of the situation
described above. The FAA has
examined the findings of the DGAC,
reviewed all available information, and
determined that AD action is necessary
for products of this type design that are
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Agencies
[Federal Register Volume 71, Number 112 (Monday, June 12, 2006)]
[Rules and Regulations]
[Pages 33595-33598]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5207]
========================================================================
Rules and Regulations
Federal Register
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Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Rules
and Regulations
[[Page 33595]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24102; Directorate Identifier 2005-NM-244-AD;
Amendment 39-14638; AD 2006-12-12]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 747-100 and -200 series
airplanes. That AD currently requires repetitive inspections for
cracking of the station 800 frame assembly, and repair if necessary.
This new AD retains the repetitive inspection requirements of the
existing AD, but expands the area to be inspected. This AD also reduces
the initial inspection threshold, removes the adjustment of the
compliance threshold and repetitive interval based on cabin
differential pressure, and adds airplanes to the applicability. This AD
results from several reports of cracks of the station 800 frame
assembly on airplanes that had accumulated fewer total flight cycles
than the initial inspection threshold in the existing AD. We are
issuing this AD to detect and correct fatigue cracks that could extend
and fully sever the frame, which could result in development of skin
cracks that could lead to rapid depressurization of the airplane.
DATES: This AD becomes effective July 17, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of July 17,
2006.
On August 30, 2001 (66 FR 38891, July 26, 2001), the Director of
the Federal Register approved the incorporation by reference of Boeing
Alert Service Bulletin 747-53A2451, including Appendix A, dated October
5, 2000.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2001-14-22, amendment
39-12333 (66 FR 38891, July 26, 2001). The existing AD applies to
certain Boeing Model 747-100 and -200 series airplanes. That NPRM was
published in the Federal Register on March 8, 2006 (71 FR 11551). That
NPRM proposed to require repetitive inspections for cracking of the
station 800 frame assembly, and repair if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Support for the Proposed AD
Air Transport Association (ATA), on behalf of its member Northwest
Airlines, concurs with the intent of the NPRM.
Requests To Remove or Revise 12-Month Grace Period From Table 2
Boeing requests that we remove the 12-month compliance time from
paragraph (h), Table 2, items (2) and (3), of the NPRM. Boeing states
that the cracking that is the subject of the NPRM is initiated and
propagated solely by cyclic loading as measured in flight cycles.
Boeing also states that calendar time has no bearing on the initiation
rate of the cracking. ATA, on behalf of Northwest Airlines, also
comments on the 12-month grace period. Northwest states that, for
operators who have planned completion of the initial inspection near
the previously defined 19,000 flight-cycle threshold in accordance with
AD 2001-14-22, the proposed 12-month grace period could result in
unscheduled out-of-service airplanes. Northwest adds that the cracking
addressed by the NPRM is attributed to fatigue, which is driven by
flight cycles rather than calendar days. Northwest therefore requests
that we change the calendar time from 12 months to 18 months, which is
consistent with the Boeing maintenance interval on Model 747 airplanes.
Northwest suggests limiting this calendar-time change to airplanes that
have not exceeded the previously mandated 19,000 total-flight-cycle
threshold. ATA states that this change would avoid disruption of
maintenance visits that were scheduled to facilitate compliance with
the existing AD.
We agree that a grace period based on calendar time is
inappropriate because, as Boeing states and ATA notes, the cracking
that is the subject of the NPRM is initiated and propagated solely by
cyclic loading as measured in flight cycles. For this reason, we
disagree with ATA's request to extend the grace period to 18 months for
certain airplanes. Instead, we have revised Table 2 of the final rule
to remove the 12-month portion of the grace period, and to include only
the compliance time based on flight cycles. This change will ensure an
equivalent level of safety and
[[Page 33596]]
alleviate concerns about unscheduled out-of-service airplanes.
Request To Clarify Expanded Inspection Requirements for Previously
Inspected Airplanes
ATA, on behalf of Northwest Airlines, also requests that, for
airplanes on which the inspections in accordance with AD 2001-14-22
have been done, we clarify that the inspection per procedures defined
in Boeing Alert Service Bulletin 747-53A2451, Revision 1, dated
November 10, 2005, be accomplished at the next scheduled repeat
inspection. Northwest states that this request complies with the
statement in the service bulletin that specifies no additional work is
necessary on airplanes previously inspected in accordance with the
initial release of the service bulletin (dated October 5, 2000), and to
do the expanded inspection at the time of the next scheduled
inspection.
We partially agree. We agree with the commenter that, for the
previously accomplished inspections, compliance with AD 2001-14-22 was
met if the inspection was accomplished in accordance with the original
release of the service bulletin (Boeing Alert Service Bulletin 747-
53A2451, including Appendix A, dated October 5, 2000). It is the intent
of the NPRM to match the service information provided by Boeing. We
disagree that any change is necessary to clarify the AD. Paragraph (f)
of the AD states that, prior to the effective date of this new AD, the
inspections may be accomplished in accordance with either the initial
release or Revision 1 of the service bulletin. After the effective date
of this AD, only Revision 1 may be used. We have not changed the AD in
this regard.
Explanation of Change to Costs of Compliance
After the NPRM was issued, we reviewed the figures we have used
over the past several years to calculate AD costs to operators. To
account for various inflationary costs in the airline industry, we find
it necessary to increase the labor rate used in these calculations from
$65 per work hour to $80 per work hour. The cost impact information,
below, reflects this increase in the specified hourly labor rate.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 900 airplanes of the affected design in the
worldwide fleet. This AD will affect about 156 airplanes of U.S.
registry.
The inspections that are specified in AD 2001-14-22, and retained
in this AD, take between 12 and 14 work hours per airplane, depending
on the airplane configuration. The average labor rate is $80 per work
hour. Based on these figures, the estimated cost of the currently
required actions is between $960 and $1,120 per airplane, per
inspection cycle.
The new actions will take between 18 and 20 work hours per
airplane, at an average labor rate of $80 per work hour. Based on these
figures, the estimated cost of the new actions specified in this AD for
U.S. operators is between $224,640 and $249,600, or between $1,440 and
$1,600 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 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 this AD:
(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.
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
removing amendment 39-12333 (66 FR 38891, July 26, 2001) and by adding
the following new airworthiness directive (AD):
2006-12-12 Boeing: Amendment 39-14638. Docket No. FAA-2006-24102;
Directorate Identifier 2005-NM-244-AD.
Effective Date
(a) This AD becomes effective July 17, 2006.
Affected ADs
(b) This AD supersedes AD 2001-14-22.
Applicability
(c) This AD applies to all Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR
series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from several reports of cracks of the
station 800 frame assembly on airplanes that had accumulated fewer
total flight cycles than the initial inspection threshold in the
existing AD. We are issuing this AD to detect and correct fatigue
cracks that could extend and fully sever the frame, which could
result in development of skin cracks that could lead to rapid
depressurization of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within
[[Page 33597]]
the compliance times specified, unless the actions have already been
done.
Restatement of the Requirements of AD 2001-14-22
Repetitive Inspections
(f) For Boeing Model 747-100, 747-100B, 747-100B SUD, -200B,
747-200C, and 747-200F series airplanes, as identified in Boeing
Alert Service Bulletin 747-53A2451, including Appendix A, dated
October 5, 2000: Do detailed, surface high-frequency eddy current
(HFEC), and open-hole HFEC inspections, as applicable, for cracking
of the station 800 frame assembly (including the inner chord strap,
angles, and exposed web) between stringers 14 and 18, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2451, including Appendix A, dated October 5, 2000;
or Boeing Alert Service Bulletin 747-53A2451, Revision 1, dated
November 10, 2005; after the effective date of this AD, only
Revision 1 of the service bulletin may be used. Except as provided
by paragraph (g) of this AD, do the inspection at the applicable
time specified in Table 1 of this AD, and repeat the inspections
thereafter at intervals not to exceed 3,000 flight cycles until the
initial inspections required by paragraph (h) of this AD are
accomplished.
Table 1.--Compliance Times
------------------------------------------------------------------------
Total flight cycles as of
August 30, 2001 (the Do the inspection in paragraph (f) of
effective date of AD 2001-14- this AD at this time
22)
------------------------------------------------------------------------
(1) Fewer than 19,000........ Before the accumulation of 19,000 total
flight cycles, or within 1,500 flight
cycles after August 30, 2001, whichever
comes later.
(2) 19,000 or more, but Within 1,500 flight cycles or 12 months
21,250 or fewer. after August 30, 2001, whichever comes
first.
(3) 21,251 or more........... Within 750 flight cycles or 12 months
after August 30, 2001, whichever comes
first.
------------------------------------------------------------------------
Adjustments to Compliance Time: Cabin Differential Pressure
(g) For Boeing Model 747-100, 747-100B, 747-100B SUD, -200B,
747-200C, and 747-200F series airplanes, as identified in Boeing
Alert Service Bulletin 747-53A2451, including Appendix A, dated
October 5, 2000, that are inspected before the effective date of
this AD: Except as provided by paragraph (i) of this AD, for the
purposes of calculating the compliance threshold and repetitive
interval for the actions required by paragraph (f) of this AD, the
number of flight cycles in which cabin differential pressure is at
2.0 pounds per square inch (psi) or less need not be counted when
determining the number of flight cycles that have occurred on the
airplane, provided that the flight cycles with momentary spikes in
cabin differential pressure above 2.0 psi are included as full
pressure cycles. For this provision to apply, all cabin pressure
records must be maintained for each airplane: No fleet-averaging of
cabin pressure is allowed.
New Requirements of this AD
Repetitive Inspections of Expanded Area at a New Reduced Threshold
(h) For all airplanes, at the applicable time specified in Table
2 of this AD, except as provided by paragraph (i) of this AD, do the
following inspections of the station 800 frame assembly in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2451, Revision 1, dated November 10, 2005: A
detailed inspection for cracking of the inner chord strap, angles,
and exposed web adjacent to the inner chords on the station 800
frame between stringer 14 and stringer 18; and surface HFEC and
open-hole HFEC inspections for cracking of the inner chord strap and
angles. Do the initial inspections at the applicable time specified
in Table 2 of this AD, and repeat the inspections thereafter at
intervals not to exceed 3,000 flight cycles. Accomplishing the
initial inspections required by this paragraph terminates the
inspection requirements of paragraph (f) of this AD.
Table 2.--Revised Compliance Times
------------------------------------------------------------------------
Total flight cycles as of the Do the inspections in paragraph (h) of
effective date of this AD this AD at this time
------------------------------------------------------------------------
(1) Fewer than 16,000........ Before the accumulation of 16,000 total
flight cycles, or within 1,500 flight
cycles after the effective date of this
AD, whichever comes later.
(2) 16,000 or more, but Within 1,500 flight cycles after the
24,250 or fewer. effective date of this AD.
(3) 24,251 or more........... Within 750 flight cycles after the
effective date of this AD.
------------------------------------------------------------------------
Adjustments to Compliance Time: Cabin Differential Pressure
(i) For the purposes of calculating the compliance threshold and
repetitive interval for actions required by paragraphs (f) and (h)
of this AD, on or after the effective date of this AD: All flight
cycles, including the number of flight cycles in which cabin
differential pressure is at 2.0 psi or less, must be counted when
determining the number of flight cycles that have occurred on the
airplane. However, for airplanes on which the repetitive interval
for the actions required by paragraph (f) of this AD have been
calculated in accordance with paragraph (g) of this AD by excluding
the number of flight cycles in which cabin differential pressure is
at 2.0 pounds psi or less: Continue to adjust the repetitive
inspection interval in accordance with paragraph (g) of this AD
until the initial inspections required by paragraph (h) of this AD
are accomplished. Thereafter, no adjustment to compliance times
based on paragraph (g) of this AD is allowed.
Repair
(j) If any cracking is detected during any inspection required
by paragraph (f) or (h) of this AD, and the service bulletin
specifies to contact Boeing for appropriate action: Before further
flight, repair using a method approved in accordance with the
procedures specified in paragraph (l) of this AD.
No Report Required
(k) Although the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2451, including Appendix A, dated October 5,
2000; and Boeing Alert Service Bulletin 747-53A2451, Revision 1,
dated November 10, 2005; describe procedures for reporting certain
information to the manufacturer, this AD does not require that
report.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, Seattle Aircraft Certification Office (ACO),
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.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane.
[[Page 33598]]
(4) AMOCs approved previously in accordance with AD 2001-14-22,
are approved as AMOCs for the corresponding provisions of paragraphs
(f) and (j) of this AD.
Material Incorporated by Reference
(m) You must use Boeing Alert Service Bulletin 747-53A2451,
including Appendix A, dated October 5, 2000; or Boeing Alert Service
Bulletin 747-53A2451, Revision 1, dated November 10, 2005; as
applicable; to perform the actions that are required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2451, Revision 1, dated November 10, 2005, in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) On August 30, 2001 (66 FR 38891, July 26, 2001), the
Director of the Federal Register approved the incorporation by
reference of Boeing Alert Service Bulletin 747-53A2451, including
Appendix A, dated October 5, 2000.
(3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, 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 May 31, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5207 Filed 6-9-06; 8:45 am]
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