Airworthiness Directives; Boeing Model 767 Airplanes, 34513-34516 [E9-16872]
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Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
328 Support Services GmbH (Formerly,
AvCraft Aerospace GmbH, Formerly
Fairchild Dornier GmbH, Formerly
Dornier Luftfahrt GmbH): Docket No.
FAA–2009–0616; Directorate Identifier
2009–NM–070–AD.
Comments Due Date
(a) We must receive comments August 17,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all 328 Support
Services GmbH Dornier Model 328–100 and
–300 airplanes, certificated in any category.
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Subject
(d) Air Transport Association (ATA) of
America Code 25: Equipment/furnishings.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
A recent incident has been reported with
a Dornier 328–100 aeroplane, where the
right-hand (RH) power lever jammed in
flight-idle position during the landing rollout. The aeroplane was stopped by excessive
braking.
The investigation by the operator revealed
that the cockpit door locking device Part
Number 001A252A3914012 had fallen off the
RH cockpit wall and blocked the RH power/
condition lever pulley/cable cluster below
the door. Although the affected aeroplane
had been modified, the technical
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investigation showed that a loose Cockpit
Door Locking device could also occur on
328–100 and 328–300 aeroplanes with a
standard installation.
This condition, if not corrected, could
cause interference with the engine- and/or
flight control cables, possibly resulting in
reduced control of the aeroplane.
For the reasons described above, this AD
requires a one-time inspection of the cockpit
door locking device and the surrounding area
[for proper installation] and the reporting of
all findings to the TC [type certificate]
holder. This AD is considered to be an
interim action and the retrofit of a new
design may be implemented later.
The corrective action is re-torquing the
attachment screws.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 3 months after the effective date
of this AD, do a detailed visual inspection of
the cockpit door locking device and the
surrounding area for proper installation, in
accordance with the Accomplishment
Instructions of 328 Support Services Service
Bulletin SB–328–25–485 or SB–328J–25–235,
both dated January 28, 2009, as applicable.
(2) If any discrepancy is found during the
inspection specified in paragraph (f)(1) of
this AD, before further flight, do the
corrective action in accordance with the
Accomplishment Instructions of 328 Support
Services Service Bulletin SB–328–25–485 or
SB–328J–25–235, both dated January 28,
2009, as applicable.
(3) Submit a report of the findings (both
positive and negative) of the inspection
required by paragraph (f)(1) of this AD to the
Manager, Attention Dept P1, 328 Support
Services GmbH, Customer Services, P.O.B.
1252, D–82231 Wessling, Fed. Rep. of
Germany; Fax +49 (0) 8153 88111–6565, at
the applicable time specified in paragraph
(f)(3)(i) or (f)(3)(ii) of this AD. The report
must include the inspection results, a
description of any discrepancies found, the
airplane serial number, and the number of
landings and flight hours on the airplane.
(i) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(ii) If the inspection was accomplished
prior to the effective date of this AD: Submit
the report within 30 days after the effective
date of this AD.
FAA AD Differences
34513
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 227–1503; fax (425)
227–1149. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) Airworthiness
Directive 2009–0082, dated April 7, 2009;
and 328 Support Services Service Bulletins
SB–328–25–485 and SB–328J–25–235, both
dated January 28, 2009; for related
information.
Issued in Renton, Washington, on July 6,
2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–16940 Filed 7–15–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0642; Directorate
Identifier 2009–NM–001–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767 Airplanes
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Standards,
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: Tom Groves, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Boeing Model 767 series airplanes. This
proposed AD would require inspections
for scribe lines in the fuselage skin at
skin lap joints, the skin at certain
external approved repairs, the skin
around external features such as
antennas, and the skin at decals; and
related investigative and corrective
actions if necessary. This proposed AD
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Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules
results from reports of scribe lines found
at skin lap joints and butt joints, around
external repairs and antennas, and at
locations where external decals had
been cut. We are proposing this AD to
detect and correct scribe lines, which
can develop into fatigue cracks in the
skin and cause sudden decompression
of the airplane.
DATES: We must receive comments on
this proposed AD by August 31, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed 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. You
may review copies of the referenced
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.
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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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6577; fax (425) 917–6590.
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SUPPLEMENTARY INFORMATION:
Relevant Service Information
Comments Invited
We have reviewed Boeing Alert
Service Bulletin 767–53A0193, Revision
1, dated April 9, 2009. The service
bulletin describes procedures for
exploratory detailed inspections to
detect scribe lines along skin lap joints,
external features, external approved
repairs, and decals. The service bulletin
specifies removing paint and sealant
from affected areas before the initial
exploratory inspection. The compliance
times for the exploratory inspections are
25,000, 37,500, and 50,000 total flight
cycles (depending on the inspection
location) plus the first scribe line
inspection opportunity; or within 4,000
flight cycles after the date of the service
bulletin; whichever occurs later.
The service bulletin specifies related
investigative actions that include
performing high frequency eddy current
or ultrasonic inspections of the scribe
lines to detect cracks, and the service
bulletin specifies corrective actions as
either repairing scribe lines and cracks
or contacting Boeing for repair
instructions and making the repair. The
service bulletin specifies to repair
cracks before further flight.
The service bulletin specifies
repairing scribe lines before further
flight, except when a limited return to
service (LRTS) program for qualifying
scribe lines would allow return to
service for a limited period before scribe
lines are repaired. The LRTS program
includes repetitive inspections to detect
cracks where scribe lines are found. To
qualify for an LRTS program, scribe
lines must meet certain criteria based on
their depth and location. The service
bulletin specifies contacting Boeing for
final repair instructions, which would
eliminate the need for the repetitive
inspections of the LRTS program. The
repetitive interval for the LRTS program
is 1,500 to 9,000 flight cycles,
depending on the depth and location of
the scribe lines and the configuration of
the airplane.
The service bulletin notes that certain
inspections would not be required
under the following conditions:
• The airplane had never been
stripped or repainted.
• The airplane had never been
stripped or repainted under the wing-tobody fairings.
• No sealant had been removed
except in accordance with the specified
sealant removal processes as given in
Appendix A of the service bulletin.
The service bulletin specifies
submitting the exploratory inspection
results to Boeing.
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2009–0642; Directorate Identifier
2009–NM–001–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received reports indicating
that scribe lines have been found by 11
operators on 13 Boeing Model 767
airplanes. Scribe lines were found at
skin lap joints, butt joints, around
external repairs and antennas, and at
locations where external decals had
been cut. Many of the scribe lines
appear to have been made when sealant
was removed as part of preparing the
airplane for repainting. The Model 767
airplanes had accumulated between
6,300 and 24,600 total flight cycles.
Although no cracks resulting from
scribe lines on Model 767 airplanes
have been reported to Boeing, fatigue
cracks can develop in the skin at scribe
line locations. Fatigue cracks, if not
corrected, could grow large and cause
sudden decompression of the airplane.
Related ADs
This proposed AD is similar to two
existing ADs. AD 2006–07–12,
amendment 39–14539 (71 FR 16211,
March 31, 2006), applies to Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. AD
2007–19–07, amendment 39–15198 (72
FR 60244, October 24, 2007), applies to
all Boeing Model 757–200, –200PF, and
–200CB series airplanes. Those ADs
require inspections to detect scribe lines
in the fuselage skin at certain lap joints,
butt joints, external repair doublers, and
other areas; and related investigative/
corrective actions if necessary. Those
actions resulted from reports of fuselage
skin cracks adjacent to the skin lap
joints on airplanes that had scribe lines.
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Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design. This proposed AD would
require accomplishing the actions
specified in the service information
described previously, except as
discussed under ‘‘Differences Between
the Proposed AD and Service Bulletin.’’
This proposed AD would also require
sending the results of the exploratory
inspections to Boeing.
Differences Between the Proposed AD
and Service Bulletin
The service bulletin specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions in
one of the following ways:
• Using a method that we approve; or
• Using data that meet the
certification basis of the airplane, and
34515
that have been approved by an
Authorized Representative for the
Boeing Commercial Airplanes
Delegation Option Authorization
Organization whom we have authorized
to make those findings.
Costs of Compliance
We estimate that this proposed AD
would affect 367 airplanes of U.S.
registry. The following table provides
the estimated costs for U.S. operators to
comply with this proposed AD.
TABLE—ESTIMATED COSTS
Action
Work hours
Average
labor rate
per hour
Parts
Cost per
product
Number of
U.S.registered
airplanes
Fleet cost
Exploratory Inspections ................
340
$80
None .............................................
$27,200
367
$9,982,400
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.
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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
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Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), and
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Jkt 217001
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Boeing: Docket No. FAA–2009–0642;
Directorate Identifier 2009–NM–001–AD.
Comments Due Date
(a) We must receive comments by August
31, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 767–
200, –300, –300F, and –400ER series
airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin
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767–53A0193, Revision 1, dated April 9,
2009.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Unsafe Condition
(e) This AD results from reports of scribe
lines found at skin lap joints, butt joints,
around external repairs and antennas, and at
locations where external decals had been cut.
We are issuing this AD to detect and correct
scribe lines, which can develop into fatigue
cracks in the skin and cause sudden
decompression 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.
Inspection
(g) At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 767–53A0193,
Revision 1, dated April 9, 2009, except as
provided in paragraph (h) of this AD, do
detailed exploratory inspections for scribe
lines of skin lap joints, butt joints, around
external repairs and antennas, and at
locations where external decals may have
been cut. Do all applicable related
investigative and corrective actions at the
times specified in the service bulletin, by
accomplishing all actions specified in the
Accomplishment Instructions of the service
bulletin, except as provided by paragraph (i)
of this AD.
Note 1: The inspection exemptions noted
in paragraph 1.E. of Boeing Alert Service
Bulletin 767–53A0193, Revision 1, dated
April 9, 2009, apply to this AD.
Exceptions to Service Bulletin Specifications
(h) Where Boeing Alert Service Bulletin
767–53A0193, Revision 1, dated April 9,
2009, specifies a compliance time after ‘‘the
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Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules
original issue date on this service bulletin,’’
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
(i) Where Boeing Alert Service Bulletin
767–53A0193, Revision 1, dated April 9,
2009, specifies to contact Boeing for
appropriate action, accomplish applicable
actions before further flight using a method
approved in accordance with the procedures
specified in paragraph (l) of 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.
Report
(j) At the applicable time specified in
paragraph (j)(1) or (j)(2) of this AD: Submit
a report of the findings (both positive and
negative) of the inspections required by
paragraph (g) of this AD. Operators may use
the reporting form contained in Appendixes
B and C, as applicable, of Boeing Alert
Service Bulletin 767–53A0193, Revision 1,
dated April 9, 2009. Send the report to
Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124–2207. The
report must contain, at a minimum, the
inspection results, a description of any
discrepancies found, the airplane serial
number, and the number of flight cycles and
flight hours on the airplane. Under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
Issued in Renton, Washington, on July 2,
2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–16872 Filed 7–15–09; 8:45 am]
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Credit for Actions Accomplished Previously
(k) Actions accomplished previously in
accordance with Boeing Alert Service
Bulletin 767–53A0193, dated November 25,
2008, are considered acceptable for
compliance with the applicable actions
specified in this AD.
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 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-ANMSeattle-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.
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15:08 Jul 15, 2009
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0613; Directorate
Identifier 2009–NM–013–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310–221, –222, –322, –324, and –325
Airplanes, and Model A300B4–620, B4–
622, B4–622R, F4–605R, and F4–622R
Airplanes, Equipped With Pratt &
Whitney PW4000 or JT9D–7R4 Series
Engines
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
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:
SUMMARY:
During the year 2000, life extension
exercise programs were launched for Airbus
A310 and A300–600 aircraft. Certification of
Extended Service Goal (ESG) is based on
analysis, except for fan cowl and thrust
reverser (T/R) latches, which are always
certified by tests.
* * * testing of the T/R door centre latch has
shown that this does not meet the
requirements for ESG.
*
*
*
*
*
The unsafe condition is possible failure
of the T/R latch and detachment of the
T/R from the airplane, which could
result in structural damage and
consequent reduced controllability of
the airplane. The proposed AD would
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require actions that are intended to
address the unsafe condition described
in the MCAI.
DATES: We must receive comments on
this proposed AD by August 17, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS–
EAW (Airworthiness Office), 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; e-mail:
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
E:\FR\FM\16JYP1.SGM
16JYP1
]]>Agencies
[Federal Register Volume 74, Number 135 (Thursday, July 16, 2009)]
[Proposed Rules]
[Pages 34513-34516]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-16872]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0642; Directorate Identifier 2009-NM-001-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Boeing Model 767 series airplanes. This proposed AD would
require inspections for scribe lines in the fuselage skin at skin lap
joints, the skin at certain external approved repairs, the skin around
external features such as antennas, and the skin at decals; and related
investigative and corrective actions if necessary. This proposed AD
[[Page 34514]]
results from reports of scribe lines found at skin lap joints and butt
joints, around external repairs and antennas, and at locations where
external decals had been cut. We are proposing this AD to detect and
correct scribe lines, which can develop into fatigue cracks in the skin
and cause sudden decompression of the airplane.
DATES: We must receive comments on this proposed AD by August 31, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed 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. You may review copies of the
referenced 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.
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6577; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0642;
Directorate Identifier 2009-NM-001-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received reports indicating that scribe lines have been
found by 11 operators on 13 Boeing Model 767 airplanes. Scribe lines
were found at skin lap joints, butt joints, around external repairs and
antennas, and at locations where external decals had been cut. Many of
the scribe lines appear to have been made when sealant was removed as
part of preparing the airplane for repainting. The Model 767 airplanes
had accumulated between 6,300 and 24,600 total flight cycles. Although
no cracks resulting from scribe lines on Model 767 airplanes have been
reported to Boeing, fatigue cracks can develop in the skin at scribe
line locations. Fatigue cracks, if not corrected, could grow large and
cause sudden decompression of the airplane.
Related ADs
This proposed AD is similar to two existing ADs. AD 2006-07-12,
amendment 39-14539 (71 FR 16211, March 31, 2006), applies to Boeing
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD
2007-19-07, amendment 39-15198 (72 FR 60244, October 24, 2007), applies
to all Boeing Model 757-200, -200PF, and -200CB series airplanes. Those
ADs require inspections to detect scribe lines in the fuselage skin at
certain lap joints, butt joints, external repair doublers, and other
areas; and related investigative/corrective actions if necessary. Those
actions resulted from reports of fuselage skin cracks adjacent to the
skin lap joints on airplanes that had scribe lines.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 767-53A0193,
Revision 1, dated April 9, 2009. The service bulletin describes
procedures for exploratory detailed inspections to detect scribe lines
along skin lap joints, external features, external approved repairs,
and decals. The service bulletin specifies removing paint and sealant
from affected areas before the initial exploratory inspection. The
compliance times for the exploratory inspections are 25,000, 37,500,
and 50,000 total flight cycles (depending on the inspection location)
plus the first scribe line inspection opportunity; or within 4,000
flight cycles after the date of the service bulletin; whichever occurs
later.
The service bulletin specifies related investigative actions that
include performing high frequency eddy current or ultrasonic
inspections of the scribe lines to detect cracks, and the service
bulletin specifies corrective actions as either repairing scribe lines
and cracks or contacting Boeing for repair instructions and making the
repair. The service bulletin specifies to repair cracks before further
flight.
The service bulletin specifies repairing scribe lines before
further flight, except when a limited return to service (LRTS) program
for qualifying scribe lines would allow return to service for a limited
period before scribe lines are repaired. The LRTS program includes
repetitive inspections to detect cracks where scribe lines are found.
To qualify for an LRTS program, scribe lines must meet certain criteria
based on their depth and location. The service bulletin specifies
contacting Boeing for final repair instructions, which would eliminate
the need for the repetitive inspections of the LRTS program. The
repetitive interval for the LRTS program is 1,500 to 9,000 flight
cycles, depending on the depth and location of the scribe lines and the
configuration of the airplane.
The service bulletin notes that certain inspections would not be
required under the following conditions:
The airplane had never been stripped or repainted.
The airplane had never been stripped or repainted under
the wing-to-body fairings.
No sealant had been removed except in accordance with the
specified sealant removal processes as given in Appendix A of the
service bulletin.
The service bulletin specifies submitting the exploratory
inspection results to Boeing.
[[Page 34515]]
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require accomplishing the actions specified in
the service information described previously, except as discussed under
``Differences Between the Proposed AD and Service Bulletin.'' This
proposed AD would also require sending the results of the exploratory
inspections to Boeing.
Differences Between the Proposed AD and Service Bulletin
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD would affect 367 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Table--Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average Cost per U.S.-
Action Work hours labor rate Parts product registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Exploratory Inspections........................ 340 $80 None............................. $27,200 367 $9,982,400
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979), and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Boeing: Docket No. FAA-2009-0642; Directorate Identifier 2009-NM-
001-AD.
Comments Due Date
(a) We must receive comments by August 31, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 767-200, -300, -300F, and -
400ER series airplanes, certificated in any category, as identified
in Boeing Alert Service Bulletin 767-53A0193, Revision 1, dated
April 9, 2009.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from reports of scribe lines found at skin
lap joints, butt joints, around external repairs and antennas, and
at locations where external decals had been cut. We are issuing this
AD to detect and correct scribe lines, which can develop into
fatigue cracks in the skin and cause sudden decompression 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.
Inspection
(g) At the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 767-53A0193,
Revision 1, dated April 9, 2009, except as provided in paragraph (h)
of this AD, do detailed exploratory inspections for scribe lines of
skin lap joints, butt joints, around external repairs and antennas,
and at locations where external decals may have been cut. Do all
applicable related investigative and corrective actions at the times
specified in the service bulletin, by accomplishing all actions
specified in the Accomplishment Instructions of the service
bulletin, except as provided by paragraph (i) of this AD.
Note 1: The inspection exemptions noted in paragraph 1.E. of
Boeing Alert Service Bulletin 767-53A0193, Revision 1, dated April
9, 2009, apply to this AD.
Exceptions to Service Bulletin Specifications
(h) Where Boeing Alert Service Bulletin 767-53A0193, Revision 1,
dated April 9, 2009, specifies a compliance time after ``the
[[Page 34516]]
original issue date on this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(i) Where Boeing Alert Service Bulletin 767-53A0193, Revision 1,
dated April 9, 2009, specifies to contact Boeing for appropriate
action, accomplish applicable actions before further flight using a
method approved in accordance with the procedures specified in
paragraph (l) of this AD.
Report
(j) At the applicable time specified in paragraph (j)(1) or
(j)(2) of this AD: Submit a report of the findings (both positive
and negative) of the inspections required by paragraph (g) of this
AD. Operators may use the reporting form contained in Appendixes B
and C, as applicable, of Boeing Alert Service Bulletin 767-53A0193,
Revision 1, dated April 9, 2009. Send the report to Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
The report must contain, at a minimum, the inspection results, a
description of any discrepancies found, the airplane serial number,
and the number of flight cycles and flight hours on the airplane.
Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501
et seq.), the Office of Management and Budget (OMB) has approved the
information collection requirements contained in this AD and has
assigned OMB Control Number 2120-0056.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
Credit for Actions Accomplished Previously
(k) Actions accomplished previously in accordance with Boeing
Alert Service Bulletin 767-53A0193, dated November 25, 2008, are
considered acceptable for compliance with the applicable actions
specified in this AD.
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
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.
Issued in Renton, Washington, on July 2, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-16872 Filed 7-15-09; 8:45 am]
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