Airworthiness Directives; Boeing Model 707 Airplanes, and Model 720 and 720B Series Airplanes, 46331-46334 [E9-20838]
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Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
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.
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:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2009–18–13 Rolls-Royce plc: Amendment
39–16009.; Docket No. FAA–2009–0771;
Directorate Identifier 2009–NE–14–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective October 14, 2009.
Affected ADs
(b) None.
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Applicability
(c) This AD applies to Rolls-Royce plc (RR)
model RB211 Trent 970–84, 970B–84, 972–
84, 972B–84, 977–84, 977B–84, and 980–84
turbofan engines that do not incorporate RR
modification Service Bulletin (SB) RB.211–
72–G025. These engines are installed on, but
not limited to, Airbus A380 airplanes.
Reason
(d) Evidence from development testing and
flight test Trent 900 engines has identified
cracking on some HP Turbine Nozzle Guide
Vane (NGV) Convex Surfaces. Analysis of test
data and review of the manufacturing process
has revealed compounding effects that may
contribute to a shortfall in component life
and an increased likelihood of premature
cracking in this region. Excessive cracking on
the Convex Surface may lead to the release
of NGV material or the blockage of Turbine
gas flow. This results in a risk of fracture to
the HP Turbine Blade.
We are issuing this AD to prevent the
release of a high-pressure (HP) turbine blade,
which could result in an engine power loss
or in-flight shut down of one or more
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engines, resulting in an inability to continue
safe flight.
Actions and Compliance
First Inspection
(e) Before accumulating 400 total cycles,
inspect the HPT NGV Convex Surfaces, in
accordance with the accomplishment
instructions in section 3.A of Rolls-Royce
RB211–Trent 900 Alert Non Modification
Service Bulletin (NMSB) RB.211–72–AF995
Revision 2, dated February 9, 2009.
Reinspection
(f) If no damage is identified at first
inspection:
(1) Repeat the inspection at intervals less
than 250 Cycles apart.
(2) If repeat inspections reveal no damage
at 1000 cycles revert to normal inspection
maintenance as detailed in the Rolls-Royce
RB211–Trent 900 Maintenance Planning
Document (MPD), and sign off this AD as
complied with; no further inspections are
required by this AD.
(g) If any damage is identified, refer to the
Table 1 and Table 2 in section 3.B. of RollsRoyce RB211–Trent 900 Alert NMSB
RB.211–72–AF995 Revision 2, dated
February 9, 2009, for reinspection intervals
and rejection criteria.
FAA AD Differences
(h) None.
Other FAA AD Provisions
(i) Alternative Methods of Compliance
(AMOCs): The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(j) Refer to MCAI EASA Airworthiness
Directive 2009–0051, dated March 5, 2009.
(k) Contact Ian Dargin, Aerospace Engineer,
Engine Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park; Burlington, MA 01803;
e-mail: ian.dargin@faa.gov; telephone (781)
238–7178; fax (781) 238–7199, for more
information about this AD.
Material Incorporated by Reference
(l) You must use RR Alert Non Mandatory
Service Bulletin RB.211–72–AF995 Revision
2, dated February 9, 2009, to do the actions
required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Rolls-Royce plc, P.O. Box
31, DERBY, DE24 8BJ, UK; telephone 44 (0)
1332 242424; fax 44 (0) 1332 249936.
(3) You may review copies at the FAA,
New England Region, 12 New England
Executive Park, Burlington, MA; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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46331
Issued in Burlington, Massachusetts, on
August 20, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E9–20830 Filed 9–8–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0476; Directorate
Identifier 2008–NM–188–AD; Amendment
39–16006; AD 2009–18–10]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 707 Airplanes, and Model 720
and 720B Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
707 airplanes, and Model 720 and 720B
series airplanes. The existing AD
currently requires repetitive detailed
inspections to detect cracks and
corrosion on any existing repairs and at
certain body stations (STA) of the
visible surfaces of the wing to body
terminal fittings including the web,
flanges, and ribs; and applicable related
investigative and corrective actions.
This new AD retains the requirements of
the existing AD and requires repetitive
ultrasonic inspections to detect any
stress corrosion cracks within the
outboard flange of the left and right
body terminal fittings at STA 820, and
related investigative and corrective
actions if necessary. This AD also
provides an optional terminating action
for the repetitive inspections. This AD
also adds two airplanes to the
applicability. This AD results from
reports of cracks found in the wing to
body terminal fittings during routine
inspections. We are issuing this AD to
detect and correct cracks and corrosion
in the body terminal fittings above and
below the floor, which could cause loss
of support for the wing and could
adversely affect the structural integrity
of the airplane.
DATES: This AD becomes effective
October 14, 2009.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of October 14, 2009.
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Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6577; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
optional terminating action for the
repetitive inspections. That NPRM also
proposed to add two airplanes to the
applicability.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2008–17–10, amendment
39–15648 (73 FR 50703, August 28,
2008). The existing AD applies to
certain Boeing Model 707 airplanes, and
Model 720 and 720B series airplanes.
That NPRM was published in the
Federal Register on May 26, 2009 (74
FR 24715). That NPRM proposed to
continue to require detailed inspections
and applicable related investigative and
corrective actions. That NPRM also
proposed to require repetitive ultrasonic
inspections to detect any stress
corrosion cracks within the outboard
flange of the left and right body terminal
fittings at station (STA) 820, and related
investigative and corrective actions if
necessary. That NPRM also proposed an
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment that has been
received on the NPRM. The commenter
concurs with the content of the NPRM.
Comments
Conclusion
We have carefully reviewed the
available data, including the comment
that has been received, and determined
that air safety and the public interest
require adopting the AD as proposed.
Costs of Compliance
There are about 128 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Average
labor rate
per hour
Action
Work hours
Inspections (required by
AD 2008–17–10).
Inspections (new required
action).
20 ...................................
$80
20 to 30, depending on
group.
Number of U.S.registered
irplanes
Cost per airplane
80
$1,600 per inspection
cycle.
$1,600 to $2,400 per inspection cycle.
11 .....................
Up to 13 ...........
Fleet cost
$17,600 per inspection
cycle.
Up to $31,200 per inspection cycle.
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Authority for This Rulemaking
Regulatory Findings
List of Subjects in 14 CFR Part 39
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.
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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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16:13 Sep 08, 2009
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Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–15648 (73
FR 50703, August 28, 2008) and by
adding the following new airworthiness
directive (AD):
■
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Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
2009–18–10 Boeing: Amendment 39–16006.
Docket No. FAA–2009–0476; Directorate
Identifier 2008–NM–188–AD.
Effective Date
(a) This AD becomes effective October 14,
2009.
Affected ADs
(b) This AD supersedes AD 2008–17–10,
amendment 39–15648.
Applicability
(c) This AD applies to Boeing Model 707–
100 long body, –200, –100B long body, and
–100B short body series airplanes; Model
707–300, –300B, –300C, and –400 series
airplanes; and Model 720 and 720B series
airplanes; certificated in any category; as
identified in Boeing 707 Alert Service
Bulletin A3524, Revision 1, dated September
18, 2008.
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Unsafe Condition
(e) This AD results from new findings of
cracks found in the wing to body terminal
fittings during routine inspections. We are
issuing this AD to detect and correct cracks
and corrosion in the body terminal fittings
above and below the floor, which could
cause loss of support for the wing and could
adversely affect the structural integrity of the
airplane.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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Restatement of Requirements of AD 2008–
17–10 With Updated Service Information
Inspections and Corrective Actions
(g) For airplanes identified in Boeing 707
Special Attention Service Bulletin 3524,
dated July 18, 2007: Within 24 months after
October 2, 2008 (the effective date of AD
2008–17–10), do detailed inspections and
applicable related investigative and
corrective actions, by accomplishing all the
actions specified in the Accomplishment
Instructions of Boeing 707 Special Attention
Service Bulletin 3524, dated July 18, 2007; or
Boeing 707 Alert Service Bulletin A3524,
Revision 1, dated September 18, 2008; except
as provided by paragraph (h) of this AD.
After the effective date of this AD, use only
Boeing 707 Alert Service Bulletin A3524,
Revision 1, dated September 18, 2008. Repeat
the detailed inspections thereafter at
intervals not to exceed 24 months. Do all
applicable related investigative and
corrective actions before further flight.
(h) If any crack or corrosion is found
during any inspection required by paragraph
(g) of this AD, and Boeing 707 Special
Attention Service Bulletin 3524, dated July
18, 2007, or Boeing 707 Alert Service
Bulletin A3524, Revision 1, dated September
18, 2008, specifies to contact Boeing for
appropriate action: Before further flight,
repair the terminal fittings using a method
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16:13 Sep 08, 2009
Jkt 217001
approved in accordance with the procedures
specified in paragraph (o) of this AD.
No Information Submission
(i) Although Boeing 707 Special Attention
Service Bulletin 3524, dated July 18, 2007;
and Boeing 707 Alert Service Bulletin A3524,
Revision 1, dated September 18, 2008;
specify to submit information to the
manufacturer, this AD does not include that
requirement.
New Requirements of This AD
Inspections
(j) For Group 1 and Group 2 airplanes
identified in Boeing 707 Alert Service
Bulletin A3524, Revision 1, dated September
18, 2008, on which a modification or repair
was done in accordance with Boeing 707/720
Service Bulletin 2912, Revision 1, dated
March 13, 1970: At the later of the times
specified in paragraphs (j)(1) and (j)(2) of this
AD, do an ultrasonic inspection to detect any
stress corrosion cracks within the outboard
flange of the left and right body terminal
fittings at body station (STA) 820, and all
applicable related investigative and
corrective actions, by accomplishing all the
actions specified in the Accomplishment
Instructions of Boeing 707 Alert Service
Bulletin A3524, Revision 1, dated September
18, 2008, except as provided by paragraph
(m) of this AD. Repeat the ultrasonic
inspection thereafter at intervals not to
exceed 24 months or 2,000 flight cycles,
whichever occurs first. Do all applicable
related investigative and corrective actions
before further flight.
(1) Within 24 months or 2,000 flight cycles
after the effective date of this AD, whichever
occurs first.
(2) Within 24 months or 2,000 flight cycles
after doing the repair or modification,
whichever occurs first.
(k) For Group 3 and Group 4 airplanes
identified in Boeing 707 Alert Service
Bulletin A3524, Revision 1, dated September
18, 2008: Within 2,000 flight cycles or 24
months after the effective date of this AD,
whichever occurs first, do an ultrasonic
inspection to detect any stress corrosion
cracks within the outboard flange of the left
and right body terminal fittings at STA 820,
and all applicable corrective actions, by
accomplishing all the actions specified in the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3524, Revision 1,
dated September 18, 2008, except as
provided by paragraph (m) of this AD. Repeat
the ultrasonic inspection thereafter at
intervals not to exceed 24 months or 2,000
flight cycles, whichever occurs first. Do all
applicable corrective actions before further
flight.
(l) For Group 4 airplanes identified in
Boeing 707 Alert Service Bulletin A3524,
Revision 1, dated September 18, 2008:
Within 24 months after the effective date of
this AD, do detailed inspections for corrosion
and cracking of the body terminal fittings at
STA 820, and all applicable related
investigative and corrective actions, by
accomplishing all the actions specified in the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3524, Revision 1,
dated September 18, 2008, except as
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46333
provided by paragraph (m) of this AD. Repeat
the detailed inspections thereafter at
intervals not to exceed 24 months. Do all
applicable related investigative and
corrective actions before further flight.
Exception to Certain Procedures
(m) If any crack or corrosion is found
during any inspection required by paragraph
(j), (k), or (l) of this AD, and Boeing 707 Alert
Service Bulletin A3524, Revision 1, dated
September 18, 2008, specifies to contact
Boeing for appropriate action: Before further
flight, repair the terminal fittings using a
method approved in accordance with the
procedures specified in paragraph (o) of this
AD.
Note 1: Boeing 707 Alert Service Bulletin
A3524, Revision 1, dated September 18,
2008, refers to Boeing 707/720 Service
Bulletin 2912, Revision 1, dated March 13,
1970, as an additional source of guidance for
doing certain inspections and repairs.
Optional Terminating Action
(n) Replacing a body terminal fitting with
a fitting made from 7075–T73 material, using
a method approved in accordance with the
procedures specified in paragraph (o) of this
AD, terminates the repetitive inspections
required by this AD for that fitting only.
Alternative Methods of Compliance
(AMOCs)
(o)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN:
Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 917–6577; fax (425)
917–6590; or, e-mail information to 9–ANM–
Seattle–ACO–AMOC–Requests@faa.gov.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(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, and the
approval must specifically refer to this AD.
Material Incorporated by Reference
(p) You must use Boeing 707 Alert Service
Bulletin A3524, Revision 1, dated September
18, 2008, to do the actions required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
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Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on August
18, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–20838 Filed 9–8–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0515; Directorate
Identifier 2008–NM–071–AD; Amendment
39–16007; AD 2009–18–11]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.28 Mark 0070 and 0100 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
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SUMMARY:
Following a red illuminated ‘‘DOOR NOT
LOCKED’’ status light indication on the door
lock indication panel after lift off, the cabin
crew operated the door lock handle. This
resulted in inadvertent opening of the
downward opening passenger door in flight.
* * *
After inspection, it was found that the false
red light might be the result of an incorrect
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16:13 Sep 08, 2009
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clearance between lever Part Number (P/N)
A26997–003 and the Up-Limit Switch. If the
Up-Limit Switch has an incorrect clearance,
the combination with cabin differential
pressure build-up after lift-off might result in
a false steady illuminating red ‘‘DOOR NOT
LOCKED’’ indication on the Door Indication
Panel. * * *
*
*
*
*
*
The unsafe condition is inadvertent
opening of the door lock handle in
flight, which could result in rapid
decompression of the airplane or
ejection of a passenger or crewmember
through the door. We are issuing this
AD to require actions to correct the
unsafe condition on these products.
DATES: This AD becomes effective
October 14, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 14, 2009.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1137; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on June 9, 2009 (74 FR 27260).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
Following a red illuminated ‘‘DOOR NOT
LOCKED’’ status light indication on the door
lock indication panel after lift off, the cabin
crew operated the door lock handle. This
resulted in inadvertent opening of the
downward opening passenger door in flight.
It appeared that the cabin crew was unaware
of the content of Fokker 70/100 Service Letter
(SL) 272. This SL informs not to operate the
door lock handle after the aircraft has started
to move or before it has come to a complete
standstill.
After inspection, it was found that the false
red light might be the result of an incorrect
clearance between lever Part Number (P/N)
A26997–003 and the Up-Limit Switch. If the
Up-Limit Switch has an incorrect clearance,
the combination with cabin differential
pressure build-up after lift-off might result in
a false steady illuminating red ‘‘DOOR NOT
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LOCKED’’ indication on the Door Indication
Panel. The original Fokker Service Bulletin
SBF100–52–044 and the associated Aircraft
Maintenance Manual (AMM) task mentioned
a clearance of 1,3 mm ± 0,3 mm. Later, based
on a trial, an improved clearance of 0,3 mm
± 0,2 mm was introduced. Both documents
have been revised for that reason. Later
production serial number aircraft with
downward opening passenger doors had the
correct clearance introduced before delivery,
but no action was taken to inspect and adjust
the clearance on previously delivered or
modified (per SBF100–52–044) serial
numbers.
Since an unsafe condition has been
identified that is likely to exist or develop on
other aircraft of the same type design, this
[EASA] Airworthiness Directive (AD)
requires two actions:
—The installation of a warning placard near
the status lights of the door lock indication
panel, instructing the cabin crew not to
operate the door handle during flight and
to inform the flight crew of the ‘‘DOOR
NOT LOCKED’’ indication; and
—A one-time inspection of the clearance
between lever P/N A26997–003 and the
Up-Limit Switch. If this clearance deviates
from the limits given in AMM task 52–71–
01–400–814–A, which is 0,3 mm ± 0,2 mm
(0.0118 inch ± 0.0079 inch), corrective
actions are required.
The unsafe condition is inadvertent
opening of the door lock handle in
flight, which could result in rapid
decompression of the airplane or
ejection of a passenger or crewmember
through the door. The corrective action
for improper clearance is adjusting the
clearance between the lever and the uplimit switch. You may obtain further
information by examining the MCAI in
the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
E:\FR\FM\09SER1.SGM
09SER1
Agencies
[Federal Register Volume 74, Number 173 (Wednesday, September 9, 2009)]
[Rules and Regulations]
[Pages 46331-46334]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-20838]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0476; Directorate Identifier 2008-NM-188-AD;
Amendment 39-16006; AD 2009-18-10]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 707 Airplanes, and Model
720 and 720B Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 707 airplanes, and Model
720 and 720B series airplanes. The existing AD currently requires
repetitive detailed inspections to detect cracks and corrosion on any
existing repairs and at certain body stations (STA) of the visible
surfaces of the wing to body terminal fittings including the web,
flanges, and ribs; and applicable related investigative and corrective
actions. This new AD retains the requirements of the existing AD and
requires repetitive ultrasonic inspections to detect any stress
corrosion cracks within the outboard flange of the left and right body
terminal fittings at STA 820, and related investigative and corrective
actions if necessary. This AD also provides an optional terminating
action for the repetitive inspections. This AD also adds two airplanes
to the applicability. This AD results from reports of cracks found in
the wing to body terminal fittings during routine inspections. We are
issuing this AD to detect and correct cracks and corrosion in the body
terminal fittings above and below the floor, which could cause loss of
support for the wing and could adversely affect the structural
integrity of the airplane.
DATES: This AD becomes effective October 14, 2009.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of October 14,
2009.
[[Page 46332]]
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6577; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2008-17-10, amendment
39-15648 (73 FR 50703, August 28, 2008). The existing AD applies to
certain Boeing Model 707 airplanes, and Model 720 and 720B series
airplanes. That NPRM was published in the Federal Register on May 26,
2009 (74 FR 24715). That NPRM proposed to continue to require detailed
inspections and applicable related investigative and corrective
actions. That NPRM also proposed to require repetitive ultrasonic
inspections to detect any stress corrosion cracks within the outboard
flange of the left and right body terminal fittings at station (STA)
820, and related investigative and corrective actions if necessary.
That NPRM also proposed an optional terminating action for the
repetitive inspections. That NPRM also proposed to add two airplanes to
the applicability.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment that has been
received on the NPRM. The commenter concurs with the content of the
NPRM.
Conclusion
We have carefully reviewed the available data, including the
comment that has been received, and determined that air safety and the
public interest require adopting the AD as proposed.
Costs of Compliance
There are about 128 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average labor Number of U.S.- registered
Action Work hours rate per hour Cost per airplane airplanes Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections (required by AD 2008-17- 20.................... $80 $1,600 per inspection 11......................... $17,600 per inspection
10). cycle. cycle.
Inspections (new required action).. 20 to 30, depending on 80 $1,600 to $2,400 per Up to 13................... Up to $31,200 per
group. inspection cycle. 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 39-15648 (73 FR 50703, August 28, 2008) and by
adding the following new airworthiness directive (AD):
[[Page 46333]]
2009-18-10 Boeing: Amendment 39-16006. Docket No. FAA-2009-0476;
Directorate Identifier 2008-NM-188-AD.
Effective Date
(a) This AD becomes effective October 14, 2009.
Affected ADs
(b) This AD supersedes AD 2008-17-10, amendment 39-15648.
Applicability
(c) This AD applies to Boeing Model 707-100 long body, -200, -
100B long body, and -100B short body series airplanes; Model 707-
300, -300B, -300C, and -400 series airplanes; and Model 720 and 720B
series airplanes; certificated in any category; as identified in
Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September
18, 2008.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Unsafe Condition
(e) This AD results from new findings of cracks found in the
wing to body terminal fittings during routine inspections. We are
issuing this AD to detect and correct cracks and corrosion in the
body terminal fittings above and below the floor, which could cause
loss of support for the wing and could adversely affect the
structural integrity of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2008-17-10 With Updated Service
Information
Inspections and Corrective Actions
(g) For airplanes identified in Boeing 707 Special Attention
Service Bulletin 3524, dated July 18, 2007: Within 24 months after
October 2, 2008 (the effective date of AD 2008-17-10), do detailed
inspections and applicable related investigative and corrective
actions, by accomplishing all the actions specified in the
Accomplishment Instructions of Boeing 707 Special Attention Service
Bulletin 3524, dated July 18, 2007; or Boeing 707 Alert Service
Bulletin A3524, Revision 1, dated September 18, 2008; except as
provided by paragraph (h) of this AD. After the effective date of
this AD, use only Boeing 707 Alert Service Bulletin A3524, Revision
1, dated September 18, 2008. Repeat the detailed inspections
thereafter at intervals not to exceed 24 months. Do all applicable
related investigative and corrective actions before further flight.
(h) If any crack or corrosion is found during any inspection
required by paragraph (g) of this AD, and Boeing 707 Special
Attention Service Bulletin 3524, dated July 18, 2007, or Boeing 707
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008,
specifies to contact Boeing for appropriate action: Before further
flight, repair the terminal fittings using a method approved in
accordance with the procedures specified in paragraph (o) of this
AD.
No Information Submission
(i) Although Boeing 707 Special Attention Service Bulletin 3524,
dated July 18, 2007; and Boeing 707 Alert Service Bulletin A3524,
Revision 1, dated September 18, 2008; specify to submit information
to the manufacturer, this AD does not include that requirement.
New Requirements of This AD
Inspections
(j) For Group 1 and Group 2 airplanes identified in Boeing 707
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008,
on which a modification or repair was done in accordance with Boeing
707/720 Service Bulletin 2912, Revision 1, dated March 13, 1970: At
the later of the times specified in paragraphs (j)(1) and (j)(2) of
this AD, do an ultrasonic inspection to detect any stress corrosion
cracks within the outboard flange of the left and right body
terminal fittings at body station (STA) 820, and all applicable
related investigative and corrective actions, by accomplishing all
the actions specified in the Accomplishment Instructions of Boeing
707 Alert Service Bulletin A3524, Revision 1, dated September 18,
2008, except as provided by paragraph (m) of this AD. Repeat the
ultrasonic inspection thereafter at intervals not to exceed 24
months or 2,000 flight cycles, whichever occurs first. Do all
applicable related investigative and corrective actions before
further flight.
(1) Within 24 months or 2,000 flight cycles after the effective
date of this AD, whichever occurs first.
(2) Within 24 months or 2,000 flight cycles after doing the
repair or modification, whichever occurs first.
(k) For Group 3 and Group 4 airplanes identified in Boeing 707
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008:
Within 2,000 flight cycles or 24 months after the effective date of
this AD, whichever occurs first, do an ultrasonic inspection to
detect any stress corrosion cracks within the outboard flange of the
left and right body terminal fittings at STA 820, and all applicable
corrective actions, by accomplishing all the actions specified in
the Accomplishment Instructions of Boeing 707 Alert Service Bulletin
A3524, Revision 1, dated September 18, 2008, except as provided by
paragraph (m) of this AD. Repeat the ultrasonic inspection
thereafter at intervals not to exceed 24 months or 2,000 flight
cycles, whichever occurs first. Do all applicable corrective actions
before further flight.
(l) For Group 4 airplanes identified in Boeing 707 Alert Service
Bulletin A3524, Revision 1, dated September 18, 2008: Within 24
months after the effective date of this AD, do detailed inspections
for corrosion and cracking of the body terminal fittings at STA 820,
and all applicable related investigative and corrective actions, by
accomplishing all the actions specified in the Accomplishment
Instructions of Boeing 707 Alert Service Bulletin A3524, Revision 1,
dated September 18, 2008, except as provided by paragraph (m) of
this AD. Repeat the detailed inspections thereafter at intervals not
to exceed 24 months. Do all applicable related investigative and
corrective actions before further flight.
Exception to Certain Procedures
(m) If any crack or corrosion is found during any inspection
required by paragraph (j), (k), or (l) of this AD, and Boeing 707
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008,
specifies to contact Boeing for appropriate action: Before further
flight, repair the terminal fittings using a method approved in
accordance with the procedures specified in paragraph (o) of this
AD.
Note 1: Boeing 707 Alert Service Bulletin A3524, Revision 1,
dated September 18, 2008, refers to Boeing 707/720 Service Bulletin
2912, Revision 1, dated March 13, 1970, as an additional source of
guidance for doing certain inspections and repairs.
Optional Terminating Action
(n) Replacing a body terminal fitting with a fitting made from
7075-T73 material, using a method approved in accordance with the
procedures specified in paragraph (o) of this AD, terminates the
repetitive inspections required by this AD for that fitting only.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S,
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone (425) 917-6577; fax (425)
917-6590; or, e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(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, and the approval must specifically refer to this
AD.
Material Incorporated by Reference
(p) You must use Boeing 707 Alert Service Bulletin A3524,
Revision 1, dated September 18, 2008, to do the actions required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of
[[Page 46334]]
this service information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; e-mail
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on August 18, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-20838 Filed 9-8-09; 8:45 am]
BILLING CODE 4910-13-P